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US3887298A - Apparatus for sealing turbine blade damper cavities - Google Patents

Apparatus for sealing turbine blade damper cavities Download PDF

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Publication number
US3887298A
US3887298A US474756A US47475674A US3887298A US 3887298 A US3887298 A US 3887298A US 474756 A US474756 A US 474756A US 47475674 A US47475674 A US 47475674A US 3887298 A US3887298 A US 3887298A
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United States
Prior art keywords
disk
face
root
blades
turbine
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Expired - Lifetime
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US474756A
Inventor
John R Hess
Joseph R Kozlin
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RTX Corp
Original Assignee
United Aircraft Corp
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Filing date
Publication date
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to US474756A priority Critical patent/US3887298A/en
Priority to CA226,568A priority patent/CA1013676A/en
Priority to IL47321A priority patent/IL47321A/en
Priority to GB22405/75A priority patent/GB1506047A/en
Priority to SE7505935A priority patent/SE7505935L/en
Priority to FR7516387A priority patent/FR2273163A1/fr
Priority to JP50065233A priority patent/JPS5113012A/ja
Application granted granted Critical
Publication of US3887298A publication Critical patent/US3887298A/en
Priority to BR4336/75D priority patent/BR7503391A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • a radial seal plate having an inclined surface which projects into a damper cavity, extends between the neck extensions of two adjacent blades in the region between the turbine disk and the platforms of the blades; the seal plate closes off one end of the damper cavity.
  • a vibration damper having two axially extending ridges separated circumferentially by a distance exceeding the gap between the platforms defining the cavity.
  • the damper has a sloped surface adjacent to the inclined surface on the seal plate.
  • FIG. 2 is a section view taken along the line 22 as shown in FIG. 1;
  • FIG. 3 is a perspective view of the seal plate which is shown in cross section in FIG. 2;
  • FIG. 4 is a perspective view of the vibration damper which is shown in cross section in FIG. 2;
  • FIG. 5 is a section view corresponding to FIG. 2 showing alternate apparatus for axially sealing the vibration damper cavity.
  • the end walls of the damper cavity are formed by a seal plate 32 on the low pressure side of the wheel assembly and by an end plate extension 34 of a vibration damper 36 on the high pressure side of the wheel assembly.
  • the seal plate 32 includes a support section 38 having an inclined surface 40 extending from the seal plate in a direction away from the axis of rotation of the wheel assembly.
  • the vibration damper has a sloped surface 42 which is essentially parallel to the inclined surface of the seal plate and a pair of platform sealing surfaces 44 as shown in FIG. 4.
  • a low pressure sideplate 46 having a long offset 48 which extends around its circumference is bolted to a low pressure face 50 of the disk and traps the seal plate between the low pressure sideplate and the disk.
  • a high pressure sideplate 52 having a short offset 54 which extends around its circumference is bolted to a high pressure face 56 of the disk and traps the end plate of the vibration damper between the high pressure sideplate and the disk as is shown in FIG. 2.
  • each blade is inserted into a fir tree shaped slot in the disk and a seal plate is positioned against the disk between two adjacent blades with the support section 38 extending into the damper cavity 28.
  • thelow pressure sideplate 46 is affixed to the disk trapping the seal plates on the wheel assembly between the long offset48 on the sideplate and the low pressure face of the disk.
  • the seal plates are adjusted to a lowered position as represented by the dotted line in FIG. 2, and a vibration damper 36 is inserted into each damper cavity.
  • a high pressure sideplate 52 is affixed to the disk trapping the end plate extensions 34 of the vibration'dampers between the short offset 54 on the sideplate and the high pressure face of the disk. Both the seal plate and the vibration damper are free to move axially and radially within limits permitted by the turbine blades, the disk and the sideplates as shown in FIG. 2.
  • each turbine blade is restrained by the disk slot and each vibration damper is restrained by the blade platforms.
  • the sloped surface 42 of each vibration damper engages and restrains the seal plate as the plate tends to move radially.
  • Each turbine blade has sufficient clearance between the blade root and the disk slot to allow limited tangential or circumferential movement of the blade when vibrationally excited.
  • the movement of the blade is resisted by the dampers, which under the influence of centrifugal force, bear against the underside of the platform of the excited blade as well as the undersides of the next adjacent blade platforms. Frictional forces at the points of contact between the dampers and the blade platforms are energy dissipative and reduce the detrimental effects of blade vibration.
  • the seal plate bears upon the vibration damper and effectively increases the mass of the damper with a corresponding increase in the damping effects.
  • the sealing surfaces 44 on the vibration damper bear against the undersides of the two adjacent turbine blades to effect a radial seal between the platforms'of two adjacent blades andto prevent the circulation working medium, which is comprised of hot gases from the main flow path, against the rim of the disk.
  • the high and low pressure sideplates acting in a conventional manner, seal the interfaces between the turbine blade roots and the disk.
  • the seal plates on the high and low pressure sides of the disk are drawn toward the vibration damper 58 by the axial components of centrifugally generated forces.
  • the embodiment of FIG. 5 is particularly attractive where the movement of the damper within the cavity due to vibration is excessive and where such movement would detrimentally increase the amount of working medium leaking between the end plate extension of the vibration damper and the high pressure face of the disk.
  • an embodiment of the invention may include a protrusion extending from the inclined surface 40 of the seal plate shown in FIG. 3, the protrusion bearing upon the sloped surface of the vibration damper.
  • the sideplates of the present invention have a greatly reduced radial width.
  • Conventional sideplates require sufficient mass at their outer diameter to resist thermal distortion as the sideplates are subjected to unequally distributed temperatures.
  • the seal plates which cover only a local area are not subjected to the severe temperature gradients and may, therefore, be fabricated from material having a lesser thickness while experiencing less thermal distortion.
  • a wheel assembly comprising:
  • a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation;
  • each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension;
  • the vibration damper further has an end plate extension which abuts the second face of the disk at the rim and the neck extensions of the two adjacent blades, and a pair of sealing surfaces, each of which is in contact with the undersurface of the platform of one of the adjacent blades, whereby the end plate extension of the vibration damper is urged against the second face of the disk by axial components of centrifugal loads during rotation of the wheel assembly and whereby the sealing surfaces of the vibration damper are held in contact with the platforms by radial components of centrifugal loads.
  • first sideplate has a circumferential offset at its periphery which engages and retains the seal plates between the offset and the first face of the disk.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Apparatus to prevent leakage of working medium through the turbine blade damper cavities of a gas turbine engine is disclosed. A radial seal plate, having an inclined surface which projects into a damper cavity, extends between the neck extensions of two adjacent blades in the region between the turbine disk and the platforms of the blades; the seal plate closes off one end of the damper cavity. Inside the cavity is a vibration damper having two axially extending ridges separated circumferentially by a distance exceeding the gap between the platforms defining the cavity. The damper has a sloped surface adjacent to the inclined surface on the seal plate. During rotation of the engine centrifugal force causes the inclined surface of the seal plate to slide along the sloped surface of the damper until the seal plate is firmly seated against the disk and the neck extensions of the two adjacent blades. Simultaneously, the gap between the blade platforms is sealed by the damper which is held in place against the undersurfaces of the blade platforms.

Description

United States Patent 11 1 Hess et al.
[ APPARATUS FOR SEALING TURBINE BLADE DAMPER CAVITIES Inventors: John R. Hess, Middletown; Joseph R. Kozlin, West Hartford, both of Conn.
United Aircraft Corporation, East Hartford, Conn.
Filed: May 30, 1974 Appl. No.: 474,756
Assignee:
References Cited UNITED STATES PATENTS 5/1961 Hunter et al. 416/193 UX 9/1961 Haworth et a1, 416/221 12/1963 Morris 416/244 A 5/1965 Davis.... 416/219 X 10/1971 Suter 416/500 X 3/1973 Nichols et a1.... 416/220 Primary ExaminerEverette A. Powell, Jr. Attorney, Agent, or Firm-Robert C. Walker [5 7] ABSTRACT Apparatus to prevent leakage of working medium through the turbine blade damper cavities of a gas turbine engine is disclosed. A radial seal plate, having an inclined surface which projects into a damper cavity, extends between the neck extensions of two adjacent blades in the region between the turbine disk and the platforms of the blades; the seal plate closes off one end of the damper cavity. Inside the cavity is a vibration damper having two axially extending ridges separated circumferentially by a distance exceeding the gap between the platforms defining the cavity. The damper has a sloped surface adjacent to the inclined surface on the seal plate. During rotation of the engine centrifugal force causes the inclined surface of the seal plate to slide along the sloped surface of the damper until the seal plate is firmly seated against the disk and the neck extensions of the two adjacent blades. Simultaneously, the gap between the blade platforms is sealed by the damper which is held in place against the undersurfaces of the blade platforms.
7 Claims, 5 Drawing Figures PATENTEUJUH3 I975 SHEET APPARATUS FOR SEALING TURBINE BLADE DAMPER CAVITIES BACKGROUND OF THE INVENTION 1. Field of the Invention This invention relates to gas turbine engines and more particularly to the axial sealing of turbine wheels.
2. Description of the Prior Art Gas turbine wheel assemblies commonly comprise a plurality of turbine blades each of which is joined to a disk through the engagement of the fir tree blade root in a corresponding disk slot and extends radially outward from the periphery of the disk. Each blade has a platform section which is spaced radially from the blade root by a neck extension. The cylinder formed by the platforms when all blades are in place defines the inner diameter wall of the working medium flow path. The platforms of two adjacent blades, in conjunction with the disk rim and the neck extensions of the two adjacent blades forms an axially oriented cavity which contains a vibration damper.
During rotation of the turbine wheel, centrifugal force urges the damper to bear upon the undersurfaces of the two adjacent blade platforms. Vibration occurring in any turbine blade is coupled into the adjacent blades through the vibration dampers. Each damper forms a mechanical bridge between the blade platforms of adjacent blades thereby tending to equalize the frequency of blade vibration throughout the wheel assembly. In addition vibratory energy is diminished by the friction between dampers and the blade platforms.
In modern gas turbine engines it is essential that the damper cavity be sealed to prevent leakage of the working medium from the main flow path and to prevent the flow of working medium, which is comprised of hot gases, against the rim of the disk.
A typical wheel construction including vibration damper cavities is shown in U.S. Pat. No. 3,666,376 to Damlis. Each damper cavity contains a vibration damper; a fully annular sideplate seals each side of the turbine disk.
' An increase in either the temperature in the turbine or the diameter of the wheel assembly causes a corresponding increase in thermal distortion of the sideplates. This distortion results in substantial leakage between the sideplate and the disk. Increasing the mass of the sideplate is one way to reduce distortion, however, the size and weight of the disk required to restrain the sideplate centrifugal loads correspondingly increase.
' Alternate apparatus for sealing the cavity between the blade platforms and the disk rim are shown in U.S. Pat. No. 3,610,778 to Suter and U.S. Pat. No. 3,1 19,595 to Wilson et al. In Wilson the open end of a baffle member formed to a cup shaped configuration surrounds the disk rim between two adjacent blade roots. The base of the cup contacts the undersides of two adjacent blade platforms and absorbs vibrational energy imparted to it by the blade platforms. The sides of the cup contact the neck extensions of the two adjacent blades thereby substantially filling the axial cavity.
Suter also discloses a vibration damper which simultaneously fills the axial cavity while damping blade vibration. Although the dampers described in Wilson and Suter substantially fill the axial cavity, apparatus for sealing the axial interface between the damper and the blade root is not provided. Similarly, in the constructions of Suter and Wilson the interface between the turbine blade roots and the disk remains unsealed thereby permitting the escape of working medium from the main flow path.
The addition of conventional annular sideplates to the wheel assemblies of Suter and Wilson for the purpose of covering the described interfaces results in a wheel assembly that is subject to the same limitations described with respect to the Damlis construction. As the size of gas turbine engines continues to increase, the larger wheel diameters are making it increasingly impractical to hold wide sideplates in surface contact with the disk and methods are necessary to appropriately secure the seal members to the turbine wheel at the blade roots.
SUMMARY OE THE INVENTION A primary object of the present invention is to prevent leakage of working medium in the axial direction across a turbine wheel assembly and to prevent the flow of hot gases against the disk rim. An additional object of the present invention is to provide damping of tangential vibrations in the blades of a turbine.
According to the present invention a sideplate affixed to a turbine disk covers the roots of the turbine blades to prevent leakage of working medium from the main flow path through the interface between the roots and the disk, and a seal plate which is responsive to centrifugal force closes off one side of the cavity formed between two adjacent turbine blades to prevent the leakage of working medium through the cavity; a vibration damper located in the cavity has a pair of sealing surfaces, each surface in contact with the underside of the platform of one of the two adjacent blades, to prevent the flow of working medium against the rim of the disk and impart friction forces to the blades to dissipate blade vibration. In accordance with a specific embodiment of the invention a support section extends from each seal plate into the damper cavity and has an inclined surface extending from the seal plate in a direction away from the engine centerline and each vibration damper has a corresponding sloped surface; during rotation of the engine the inclined surface of the seal plate and the sloped surface of the vibration damper are engaged by centrifugal forces which drive the seal plate in a direction parallel to the sloped surface of the vibration damper until the seal plate abuts the disk and the neck extensions of the two adjacent blades.
Primary features of the present invention are the individual seal plates which cover the vibration damper cavities and the annular sideplates having a short radial width which is sufficient to cover the interface between the turbine blade root and the disk. In one embodiment each seal plate has an inclined surface which, under centrifugal loading conditions, cooperates with a correspondingly sloped surface on the vibration damper to drive the seal plate against the surface of the turbine disk and theneck extensions of two adjacent blades. A pair of sealing surfaces on each blade vibration damper form a radial seal in the gap between against blade platforms, each sealing surface contacting the underside of the platform of one of the adjacent blades. An end plate extension on the vibration damper is driven against the surface of the turbine disk and the neck extensions of the two adjacent blades.
A principal advantage of the present invention is a reduction in a quantity of working medium leaking across the wheel assembly. Also the wheel construction in accordance with the present invention results in a significantly reduced mass at the outer diameter of the sideplates. Relative movement between the damper and the seal plate along the slope surface of the damper is encouraged by vibrations of the damper which interrupt the friction forces at the interface between the damper and the seal plate.
The foregoing and other objects, features and advantages of the present invention will become more apparent in the light of the following detailed description of the preferred embodiments thereof as illustrated in the accompanying drawing.
BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is a partially broken away rear elevation view of a portion of a turbine wheel assembly showing apparatus for axially sealing the vibration damper cavity and the interface between the blade root and the disk;
FIG. 2 is a section view taken along the line 22 as shown in FIG. 1;
FIG. 3 is a perspective view of the seal plate which is shown in cross section in FIG. 2;
FIG. 4 is a perspective view of the vibration damper which is shown in cross section in FIG. 2; and
FIG. 5 is a section view corresponding to FIG. 2 showing alternate apparatus for axially sealing the vibration damper cavity.
DESCRIPTION OF THE PREFERRED EMBODIMENT FIG. 1 shows a turbine wheel assembly including a disk 12 having a rim 14 and a plurality of fir tree type connecting slots 16 each of which engages a correspondingly shaped root 18 of a blade 20. Each blade has a platform section 22 spaced apart from the root by a neck extention 24. The neck extensions of two adjacent blades form the sidewalls 26 of an axially oriented damper cavity 28. The rim forms the inner wall of the cavity and the undersides 30 of the platforms of the two adjacent blades form the outer wall of the cavity. As shown in FIG. 2, the end walls of the damper cavity are formed by a seal plate 32 on the low pressure side of the wheel assembly and by an end plate extension 34 of a vibration damper 36 on the high pressure side of the wheel assembly. As shown in FIG. 3 the seal plate 32 includes a support section 38 having an inclined surface 40 extending from the seal plate in a direction away from the axis of rotation of the wheel assembly. The vibration damper has a sloped surface 42 which is essentially parallel to the inclined surface of the seal plate and a pair of platform sealing surfaces 44 as shown in FIG. 4. A low pressure sideplate 46 having a long offset 48 which extends around its circumference is bolted to a low pressure face 50 of the disk and traps the seal plate between the low pressure sideplate and the disk. Similarly, a high pressure sideplate 52 having a short offset 54 which extends around its circumference is bolted to a high pressure face 56 of the disk and traps the end plate of the vibration damper between the high pressure sideplate and the disk as is shown in FIG. 2.
To assemble the turbine wheel, the root of each blade is inserted into a fir tree shaped slot in the disk and a seal plate is positioned against the disk between two adjacent blades with the support section 38 extending into the damper cavity 28. With all the blades and seal plates in position thelow pressure sideplate 46 is affixed to the disk trapping the seal plates on the wheel assembly between the long offset48 on the sideplate and the low pressure face of the disk. The seal plates are adjusted to a lowered position as represented by the dotted line in FIG. 2, and a vibration damper 36 is inserted into each damper cavity. A high pressure sideplate 52 is affixed to the disk trapping the end plate extensions 34 of the vibration'dampers between the short offset 54 on the sideplate and the high pressure face of the disk. Both the seal plate and the vibration damper are free to move axially and radially within limits permitted by the turbine blades, the disk and the sideplates as shown in FIG. 2. I
During operation of the gas turbine engine, centrifugal loads force the individual components radially away from the axis of rotation. Each turbine blade is restrained by the disk slot and each vibration damper is restrained by the blade platforms. The sloped surface 42 of each vibration damper engages and restrains the seal plate as the plate tends to move radially.
Each turbine blade has sufficient clearance between the blade root and the disk slot to allow limited tangential or circumferential movement of the blade when vibrationally excited. During a period of vibrational excitation, the movement of the blade is resisted by the dampers, which under the influence of centrifugal force, bear against the underside of the platform of the excited blade as well as the undersides of the next adjacent blade platforms. Frictional forces at the points of contact between the dampers and the blade platforms are energy dissipative and reduce the detrimental effects of blade vibration. The seal plate bears upon the vibration damper and effectively increases the mass of the damper with a corresponding increase in the damping effects. The sealing surfaces 44 on the vibration damper bear against the undersides of the two adjacent turbine blades to effect a radial seal between the platforms'of two adjacent blades andto prevent the circulation working medium, which is comprised of hot gases from the main flow path, against the rim of the disk.
The centrifugal force due to each seal plate during rotationis transferred to the corresponding vibration damper across the slope surface 42. The force has a component which tends to draw the seal plate and the vibration damper together until the seal plate and the end plate extension 34 on the vibration damper abut the low and high pressure faces respectively of the disk. When the sloped surface of the vibration damper and inclined surface of the seal plate are in contact friction forces resist their relative movement. However, as the damper vibrates the contact is interrupted thereby reducing the frictional resistance and permitting the seal plate and damper to reposition by sliding.
The high and low pressure sideplates, acting in a conventional manner, seal the interfaces between the turbine blade roots and the disk.
The alternative embodiment shown in FIG. 5 incorporates seal plates on boththe high and low pressure sides of the wheel assembly. An independent vibration damper 58 having a pair of sloped surfaces 60 is located within the damper cavity. A pair of the seal plates 32 engage the damper, the inclined surface 38 of each seal plate engaging the correspondingly sloped surface on the damper. l
The seal plates on the high and low pressure sides of the disk are drawn toward the vibration damper 58 by the axial components of centrifugally generated forces. The embodiment of FIG. 5 is particularly attractive where the movement of the damper within the cavity due to vibration is excessive and where such movement would detrimentally increase the amount of working medium leaking between the end plate extension of the vibration damper and the high pressure face of the disk.
Although the contact between the seal plate and the vibration damper has been described with respect to engaged surfaces a construction where the contact is at a point meeting an inclined surface is equally effective. For example, an embodiment of the invention may include a protrusion extending from the inclined surface 40 of the seal plate shown in FIG. 3, the protrusion bearing upon the sloped surface of the vibration damper.
The sideplates of the present invention have a greatly reduced radial width. Conventional sideplates require sufficient mass at their outer diameter to resist thermal distortion as the sideplates are subjected to unequally distributed temperatures. The seal plates which cover only a local area are not subjected to the severe temperature gradients and may, therefore, be fabricated from material having a lesser thickness while experiencing less thermal distortion.
The axial forces generated by the seal plate during rotation are sufficient to hold the seal plate and the end plate extension of the vibration damper in surface contact with the turbine disk and the turbine blade roots, precluding a requirement for additional attaching members.
Although the invention has been described with respect to an axially oriented damper cavity the concepts disclosed equally apply where the cavity is oriented diagonal to the axis of the turbine wheel.
It should be understood by those skilled in the art that the foregoing and other changes and omissions in the form and detail thereof can be made therein without departing from the spirit and the scope of the invention.
Having thus described a typical embodiment of our invention, that which we claim as new and desire to secure by Letters Patent of the United States is:
1. In a gas turbine having an axis of rotation, a wheel assembly comprising:
a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation;
a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension;
a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades;
a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the sea] plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly;
a first sideplate which is in surface contact with the first face of the disk and covers the root portions of a plurality of turbine blades; and
a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
2. The invention according to claim 1 wherein the support section has an inclined surface substantially parallel to, and in contact with, the sloped surface of the vibration damper.
3. The invention according to claim 1 wherein the vibration damper further has an end plate extension which abuts the second face of the disk at the rim and the neck extensions of the two adjacent blades, and a pair of sealing surfaces, each of which is in contact with the undersurface of the platform of one of the adjacent blades, whereby the end plate extension of the vibration damper is urged against the second face of the disk by axial components of centrifugal loads during rotation of the wheel assembly and whereby the sealing surfaces of the vibration damper are held in contact with the platforms by radial components of centrifugal loads.
4. The invention according to claim 1 wherein the first sideplate has a circumferential offset at its periphery which engages and retains the seal plates between the offset and the first face of the disk.
5. The invention according to claim 1 wherein the second sideplate has a circumferential offset at its periphery which engages and retains the vibration dampers between the offset and the second face of the disk.
6. In a gas turbine engine having an axis of rotation, a wheel assembly of the type wherein a plurality of blades is attached to a turbine disk and extend radially from the disk, the disk having a face which is substantially perpendicular to the axis of rotation and a circumferentially extending rim with root connecting means spaced about the rim, and each blade having a root which engages the root connecting means of the disk and a blade platform joined to the root by a neck extension, and wherein a plurality of seal plates is held in contact with the disk face and the neck extensions of two adjacent blades to prevent the leakage of working medium in the axial direction across the wheel assembly, the improvement which comprises:
means responsive to centrifugal force to urge each seal plate against the face of the disk and to damp vibration in the blades.
7. The invention according to claim 6 wherein the means responsive to centrifugal force comprises:
a support which is integral with the seal plate, ex-
tends axially between the neck extensions of two adjacent blades, and has a surface which extends from the seal plate and is inclined in a direction away from the axis of rotation; and
a vibration damper which is axially restrained by the disk and has a sloped surface substantially parallel to, and in contact with, the inclined surface of the seal plate.
UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION PATENT NO. 1 7,298
DATED June 3, 1975 |NVENTOR(S) 1 John R. Hess and Joseph R. Kozlin It is certified that error appears in the above-identified patent and that said Letters Patent are hereby corrected as shown below:
Column 5, line 38, before the Word "It" insert --Although the invention has been shown and described with respect to the preferred Q embodiments thereof,--
Signed and Sealed this seventh Day of omeerzws [SEAL] Attest:
RUTH C. MASON C. MARSHALL DANN' Arresting Officer Commissioner ufParents and Trademarks

Claims (7)

1. In a gas turbine having an axis of rotation, a wheel assembly comprising: a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation; a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension; a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades; a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the seal plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly; a first sideplate which is in surface contact with the first face of the disk and covers the root portions of a plurality of turbine blades; and a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
1. In a gas turbine having an axis of rotation, a wheel assembly comprising: a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation; a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension; a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades; a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the seal plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly; a first sideplate which is in surface contact with the first face of the disk and covers the root portions of a plurality of turbine blades; and a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
2. The invention according to claim 1 wherein the support section has an inclined surface substantially parallel to, and in contact with, the sloped surface of the vibration damper.
3. The invention according to claim 1 wherein the vibration damper further has an end plate extension which abuts the second face of the disk at the rim and the neck extensions of the two adjacent blades, and a pair of sealing surfaces, each of which is in contact with the undersurface of the platform of one of the adjacent blades, whereby the end plate extension of the vibration damper is urged against the second face of the disk by axial components of centrifugal loads during rotation of the wheel assembly and whereby the sealing surfaces of the vibration damper are held in contact with the platforms by radial components of centrifugal loads.
4. The invention according to claim 1 wherein the first sideplate has a circumferential offset at its periphery which engages and retains the seal plates between the offset and the first face of the disk.
5. The invention according To claim 1 wherein the second sideplate has a circumferential offset at its periphery which engages and retains the vibration dampers between the offset and the second face of the disk.
6. In a gas turbine engine having an axis of rotation, a wheel assembly of the type wherein a plurality of blades is attached to a turbine disk and extend radially from the disk, the disk having a face which is substantially perpendicular to the axis of rotation and a circumferentially extending rim with root connecting means spaced about the rim, and each blade having a root which engages the root connecting means of the disk and a blade platform joined to the root by a neck extension, and wherein a plurality of seal plates is held in contact with the disk face and the neck extensions of two adjacent blades to prevent the leakage of working medium in the axial direction across the wheel assembly, the improvement which comprises: means responsive to centrifugal force to urge each seal plate against the face of the disk and to damp vibration in the blades.
US474756A 1974-05-30 1974-05-30 Apparatus for sealing turbine blade damper cavities Expired - Lifetime US3887298A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US474756A US3887298A (en) 1974-05-30 1974-05-30 Apparatus for sealing turbine blade damper cavities
CA226,568A CA1013676A (en) 1974-05-30 1975-05-08 Apparatus for sealing turbine blade damper cavities
IL47321A IL47321A (en) 1974-05-30 1975-05-20 Turbine engine
GB22405/75A GB1506047A (en) 1974-05-30 1975-05-22 Gas turbine having axial sealing of a turbine wheel
SE7505935A SE7505935L (en) 1974-05-30 1975-05-26 APPLIANCE FOR SEALING TURBINES
FR7516387A FR2273163A1 (en) 1974-05-30 1975-05-27
JP50065233A JPS5113012A (en) 1974-05-30 1975-05-30
BR4336/75D BR7503391A (en) 1974-05-30 1975-06-28 GAS TURBINE IMPROVEMENT

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US474756A US3887298A (en) 1974-05-30 1974-05-30 Apparatus for sealing turbine blade damper cavities

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US3887298A true US3887298A (en) 1975-06-03

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JP (1) JPS5113012A (en)
BR (1) BR7503391A (en)
CA (1) CA1013676A (en)
FR (1) FR2273163A1 (en)
GB (1) GB1506047A (en)
IL (1) IL47321A (en)
SE (1) SE7505935L (en)

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FR2289726A1 (en) * 1974-10-29 1976-05-28 United Technologies Corp TURBINE ROTOR
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
US4108571A (en) * 1976-02-11 1978-08-22 Rolls-Royce Limited Bladed rotor assembly for a gas turbine engine
FR2451451A1 (en) * 1979-03-10 1980-10-10 Rolls Royce BLADE ROTOR WITH A SEALING DEVICE FOR A GAS TURBINE ENGINE
FR2523208A1 (en) * 1982-03-12 1983-09-16 Snecma DEVICE FOR DAMPING MOBILE TURBINE BLADE VIBRATIONS
DE3307571A1 (en) * 1982-03-12 1983-09-22 United Technologies Corp., 06101 Hartford, Conn. BLADE SHOCK ABSORBER AND DAMPING DEVICE
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
EP0169800A1 (en) * 1984-07-23 1986-01-29 United Technologies Corporation Turbine cover-seal assembly
US4568247A (en) * 1984-03-29 1986-02-04 United Technologies Corporation Balanced blade vibration damper
FR2586061A1 (en) * 1985-08-08 1987-02-13 Snecma MULTI-FUNCTION LABYRINTH DOOR DISK FOR TURBOMACHINE ROTOR
US4723889A (en) * 1985-07-16 1988-02-09 Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." Fan or compressor angular clearance limiting device
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5052890A (en) * 1989-02-23 1991-10-01 Rolls-Royce Plc Device for damping vibrations in turbomachinery blades
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5284421A (en) * 1992-11-24 1994-02-08 United Technologies Corporation Rotor blade with platform support and damper positioning means
WO1994012772A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade seal
WO1994012773A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade damper
US5339619A (en) * 1992-08-31 1994-08-23 United Technologies Corporation Active cooling of turbine rotor assembly
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
EP0709549A1 (en) * 1994-10-26 1996-05-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Bladed rotor especially for a turbomachine
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US6139277A (en) * 1998-12-22 2000-10-31 Air Concepts, Inc. Motorized fan
US6273683B1 (en) 1999-02-05 2001-08-14 Siemens Westinghouse Power Corporation Turbine blade platform seal
US20070258816A1 (en) * 2005-09-26 2007-11-08 Pratt & Whitney Canada Corp. Blades for a gas turbine engine with integrated sealing plate and method
US20080181779A1 (en) * 2007-01-25 2008-07-31 Siemens Power Generation, Inc. Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies
EP1522677A3 (en) * 2003-10-08 2008-09-03 United Technologies Corporation Blade damper
EP2058526A1 (en) * 2007-11-12 2009-05-13 Snecma Unit of a fan vane and its buffer spring, buffer spring of a fan vane and method of calibrating the buffer spring
WO2010071496A1 (en) * 2008-12-18 2010-06-24 Volvo Aero Corporation Gas turbine composite workpiece to be used in gas turbine engine
DE102009011879A1 (en) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integrally bladed rotor and method of making an integrally bladed rotor
US8128371B2 (en) 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
US20120301298A1 (en) * 2011-05-23 2012-11-29 Rolls-Royce Plc Balancing of rotatable components
US20130064668A1 (en) * 2011-09-08 2013-03-14 II Anthony Reid Paige Turbine rotor blade assembly and method of assembling same
US20130108446A1 (en) * 2011-10-28 2013-05-02 General Electric Company Thermal plug for turbine bucket shank cavity and related method
US20130323031A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
US20130323058A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
EP2848770A1 (en) * 2013-09-17 2015-03-18 MTU Aero Engines GmbH Impeller blade of an axial turbo-machine and damping element
EP2873807A1 (en) * 2013-11-18 2015-05-20 Siemens Aktiengesellschaft Cover plate, rotor blade, wheel disc, bolt and gas turbine
WO2017123206A1 (en) * 2016-01-12 2017-07-20 Siemens Aktiengesellschaft Flexible damper for turbine blades
US20170314397A1 (en) * 2016-04-27 2017-11-02 MTU Aero Engines AG Turbomachine blade assembly
US20180274381A1 (en) * 2017-03-23 2018-09-27 General Electric Company Gas turbine engine component incorporating a seal slot
US10202853B2 (en) 2013-09-11 2019-02-12 General Electric Company Ply architecture for integral platform and damper retaining features in CMC turbine blades
US10648352B2 (en) 2012-06-30 2020-05-12 General Electric Company Turbine blade sealing structure
CN111448365A (en) * 2017-12-12 2020-07-24 赛峰直升机发动机公司 Damper for a turbine rotor blade

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FR2289726A1 (en) * 1974-10-29 1976-05-28 United Technologies Corp TURBINE ROTOR
US4108571A (en) * 1976-02-11 1978-08-22 Rolls-Royce Limited Bladed rotor assembly for a gas turbine engine
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
FR2451451A1 (en) * 1979-03-10 1980-10-10 Rolls Royce BLADE ROTOR WITH A SEALING DEVICE FOR A GAS TURBINE ENGINE
GB2116641A (en) * 1982-03-12 1983-09-28 United Technologies Corp Blade damper seal
DE3307571A1 (en) * 1982-03-12 1983-09-22 United Technologies Corp., 06101 Hartford, Conn. BLADE SHOCK ABSORBER AND DAMPING DEVICE
FR2523208A1 (en) * 1982-03-12 1983-09-16 Snecma DEVICE FOR DAMPING MOBILE TURBINE BLADE VIBRATIONS
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4480959A (en) * 1982-03-12 1984-11-06 S.N.E.C.M.A. Device for damping vibrations of mobile turbine blades
EP0089272A1 (en) * 1982-03-12 1983-09-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbine rotor comprising a damping device for the turbine blades
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US4568247A (en) * 1984-03-29 1986-02-04 United Technologies Corporation Balanced blade vibration damper
EP0169800A1 (en) * 1984-07-23 1986-01-29 United Technologies Corporation Turbine cover-seal assembly
US4659285A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine cover-seal assembly
US4723889A (en) * 1985-07-16 1988-02-09 Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." Fan or compressor angular clearance limiting device
FR2586061A1 (en) * 1985-08-08 1987-02-13 Snecma MULTI-FUNCTION LABYRINTH DOOR DISK FOR TURBOMACHINE ROTOR
EP0214876A1 (en) * 1985-08-08 1987-03-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Multifunctional support disc for a labyrinth seal of a turbo machine rotor
US4668167A (en) * 1985-08-08 1987-05-26 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Multifunction labyrinth seal support disk for a turbojet engine rotor
WO1988005121A1 (en) * 1986-12-29 1988-07-14 United Technologies Corporation Interblade seal for turbomachine rotor
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5052890A (en) * 1989-02-23 1991-10-01 Rolls-Royce Plc Device for damping vibrations in turbomachinery blades
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
US5339619A (en) * 1992-08-31 1994-08-23 United Technologies Corporation Active cooling of turbine rotor assembly
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5284421A (en) * 1992-11-24 1994-02-08 United Technologies Corporation Rotor blade with platform support and damper positioning means
WO1994012772A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade seal
WO1994012773A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade damper
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
EP0709549A1 (en) * 1994-10-26 1996-05-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Bladed rotor especially for a turbomachine
FR2726323A1 (en) * 1994-10-26 1996-05-03 Snecma ASSEMBLY OF A ROTARY DISK AND AUBES, ESPECIALLY USED IN A TURBOMACHINE
US5599170A (en) * 1994-10-26 1997-02-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Seal for gas turbine rotor blades
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US6139277A (en) * 1998-12-22 2000-10-31 Air Concepts, Inc. Motorized fan
US6273683B1 (en) 1999-02-05 2001-08-14 Siemens Westinghouse Power Corporation Turbine blade platform seal
EP1522677A3 (en) * 2003-10-08 2008-09-03 United Technologies Corporation Blade damper
US7484936B2 (en) 2005-09-26 2009-02-03 Pratt & Whitney Canada Corp. Blades for a gas turbine engine with integrated sealing plate and method
US20070258816A1 (en) * 2005-09-26 2007-11-08 Pratt & Whitney Canada Corp. Blades for a gas turbine engine with integrated sealing plate and method
US7762780B2 (en) 2007-01-25 2010-07-27 Siemens Energy, Inc. Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies
US20080181779A1 (en) * 2007-01-25 2008-07-31 Siemens Power Generation, Inc. Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies
US8128371B2 (en) 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
FR2923557A1 (en) * 2007-11-12 2009-05-15 Snecma Sa BLOWER DRAWER ASSEMBLY AND ITS SHOCK ABSORBER, BLOWER DAMPER AND METHOD FOR CALIBRATING THE SHOCK ABSORBER
RU2476683C2 (en) * 2007-11-12 2013-02-27 Снекма Blower blade assembly with damper, blower blade damper, and method of damper calibration
US8113783B2 (en) 2007-11-12 2012-02-14 Snecma Assembly of a fan blade and of its damper, fan blade damper and method for calibrating the damper
US20090123286A1 (en) * 2007-11-12 2009-05-14 Snecma Assembly of a fan blade and of its damper, fan blade damper and method for calibrating the damper
EP2058526A1 (en) * 2007-11-12 2009-05-13 Snecma Unit of a fan vane and its buffer spring, buffer spring of a fan vane and method of calibrating the buffer spring
WO2010071496A1 (en) * 2008-12-18 2010-06-24 Volvo Aero Corporation Gas turbine composite workpiece to be used in gas turbine engine
DE102009011879A1 (en) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integrally bladed rotor and method of making an integrally bladed rotor
US20120301298A1 (en) * 2011-05-23 2012-11-29 Rolls-Royce Plc Balancing of rotatable components
US8974185B2 (en) * 2011-05-23 2015-03-10 Rolls-Royce Plc Balancing of rotatable components
US10287897B2 (en) * 2011-09-08 2019-05-14 General Electric Company Turbine rotor blade assembly and method of assembling same
US20130064668A1 (en) * 2011-09-08 2013-03-14 II Anthony Reid Paige Turbine rotor blade assembly and method of assembling same
US20130108446A1 (en) * 2011-10-28 2013-05-02 General Electric Company Thermal plug for turbine bucket shank cavity and related method
US9366142B2 (en) * 2011-10-28 2016-06-14 General Electric Company Thermal plug for turbine bucket shank cavity and related method
US9650901B2 (en) * 2012-05-31 2017-05-16 Solar Turbines Incorporated Turbine damper
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US20130323058A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
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US20170314397A1 (en) * 2016-04-27 2017-11-02 MTU Aero Engines AG Turbomachine blade assembly
US20180274381A1 (en) * 2017-03-23 2018-09-27 General Electric Company Gas turbine engine component incorporating a seal slot
US10941671B2 (en) * 2017-03-23 2021-03-09 General Electric Company Gas turbine engine component incorporating a seal slot
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CN111448365B (en) * 2017-12-12 2023-02-28 赛峰直升机发动机公司 Vibration damper for a turbine rotor blade

Also Published As

Publication number Publication date
IL47321A0 (en) 1975-07-28
BR7503391A (en) 1976-04-27
CA1013676A (en) 1977-07-12
JPS5113012A (en) 1976-02-02
GB1506047A (en) 1978-04-05
FR2273163A1 (en) 1975-12-26
SE7505935L (en) 1975-12-01
IL47321A (en) 1977-07-31

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