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GB1082634A - Improvements in or relating to sealing rings in turbines - Google Patents

Improvements in or relating to sealing rings in turbines

Info

Publication number
GB1082634A
GB1082634A GB4695564A GB4695564A GB1082634A GB 1082634 A GB1082634 A GB 1082634A GB 4695564 A GB4695564 A GB 4695564A GB 4695564 A GB4695564 A GB 4695564A GB 1082634 A GB1082634 A GB 1082634A
Authority
GB
United Kingdom
Prior art keywords
chamber
segments
ports
pressure
sealing ring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB4695564A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Licentia Patent Verwaltungs GmbH
Original Assignee
Licentia Patent Verwaltungs GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Licentia Patent Verwaltungs GmbH filed Critical Licentia Patent Verwaltungs GmbH
Publication of GB1082634A publication Critical patent/GB1082634A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor

Landscapes

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

Abstract

1,082,634. Turbines. LICENTIA PATENTVERWALTUNGS - G. m. b.H. Nov. 18, 1964 [Nov.19, 1963], No. 46955/64. Heading F1T. For effecting adjustment of the clearance gap 17, Fig. 1, between an axial flow turbine rotor 10 and a sealing ring, the sealing ring comprises a number of segments 16, each of which is radially adjustable by varying the pressure of a hydraulic fluid in an annular chamber 21 surrounding the sealing ring and being formed by a part 12 of the turbine casing. Each segment 16 is formed with two radially extending bolts 22 and 23 which pass through bores 25 in the part 12, between which part and nuts 26 and 27 is clamped an inwardly bowed leaf spring 46. From an admission chamber 36, pressure fluid may be introduced into the chamber 21 via ports 32 and 30 to urge the segments 16, against the force of springs 46 to their radially innermost positions, shown in Fig. 1. The minimum value of the gap 17 may be varied by adjusting the nuts 26 and 27. The pressure in the chamber 21 may be relieved through ports 30, 33 and 37 via valve 35, the springs 46 and the pressure in the working medium flow channel then urging the segments 16 to their radially outermost positions, when they abut the part 12 as shown in Fig. 2. As an alternative to the ports 32, ports 43 and 44 and valve 50 may be provided. Annular sealing rings (not shown) may be provided between the segments 16 and the side walls 18, 19 of the annular groove in the part 12 which forms the chamber 21.
GB4695564A 1963-11-19 1964-11-18 Improvements in or relating to sealing rings in turbines Expired GB1082634A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE1963L0046369 DE1286810B (en) 1963-11-19 1963-11-19 Rotor blade radial gap cover ring of an axial turbine machine, in particular a gas turbine

Publications (1)

Publication Number Publication Date
GB1082634A true GB1082634A (en) 1967-09-06

Family

ID=7271580

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4695564A Expired GB1082634A (en) 1963-11-19 1964-11-18 Improvements in or relating to sealing rings in turbines

Country Status (3)

Country Link
CH (1) CH418731A (en)
DE (1) DE1286810B (en)
GB (1) GB1082634A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2509373A1 (en) * 1981-07-11 1983-01-14 Rolls Royce ADJUSTABLE WRAPPING CROWN FOR MOBILE BLADES OF A GAS TURBINE ENGINE
FR2540939A1 (en) * 1983-02-10 1984-08-17 Snecma SEALING RING FOR A TURBINE ROTOR OF A TURBOMACHINE AND TURBOMACHINE INSTALLATION PROVIDED WITH SUCH RINGS
FR2589520A1 (en) * 1985-10-30 1987-05-07 Snecma Turbine housing with heat accumulator - has spaces between outer and inner casings filled with thermal material e.g. cellular blocks based on titanium or aluminium
GB2244523A (en) * 1990-05-31 1991-12-04 Gen Electric Gas turbine shroud assembly
GB2404953A (en) * 2003-08-15 2005-02-16 Rolls Royce Plc Blade tip clearance system
GB2418955A (en) * 2004-07-09 2006-04-12 United Technologies Corp Blade tip clearance control
EP2078822A1 (en) * 2008-01-11 2009-07-15 Snecma Gas-turbine engine with valve for connecting two enclosures

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2922835C2 (en) * 1979-06-06 1985-06-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Circumferential gap seal on axial flow machines
US4329114A (en) * 1979-07-25 1982-05-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active clearance control system for a turbomachine
DE2931766C2 (en) * 1979-08-04 1982-08-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Sealing device for the free blade ends of an adjustable diffuser of a gas turbine
US5104287A (en) * 1989-09-08 1992-04-14 General Electric Company Blade tip clearance control apparatus for a gas turbine engine
US5056988A (en) * 1990-02-12 1991-10-15 General Electric Company Blade tip clearance control apparatus using shroud segment position modulation
DE102008060706A1 (en) * 2008-12-05 2010-06-10 Man Turbo Ag Nozzle segment for a steam turbine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE543709A (en) * 1954-12-16
BE556215A (en) * 1956-03-28 1957-04-15

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2509373A1 (en) * 1981-07-11 1983-01-14 Rolls Royce ADJUSTABLE WRAPPING CROWN FOR MOBILE BLADES OF A GAS TURBINE ENGINE
US4472108A (en) * 1981-07-11 1984-09-18 Rolls-Royce Limited Shroud structure for a gas turbine engine
FR2540939A1 (en) * 1983-02-10 1984-08-17 Snecma SEALING RING FOR A TURBINE ROTOR OF A TURBOMACHINE AND TURBOMACHINE INSTALLATION PROVIDED WITH SUCH RINGS
EP0119881A1 (en) * 1983-02-10 1984-09-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gas turbine rotor sealing ring and a turbo machine installation provided with such a ring
FR2589520A1 (en) * 1985-10-30 1987-05-07 Snecma Turbine housing with heat accumulator - has spaces between outer and inner casings filled with thermal material e.g. cellular blocks based on titanium or aluminium
GB2244523A (en) * 1990-05-31 1991-12-04 Gen Electric Gas turbine shroud assembly
US5127793A (en) * 1990-05-31 1992-07-07 General Electric Company Turbine shroud clearance control assembly
GB2244523B (en) * 1990-05-31 1993-09-08 Gen Electric Turbine shroud assembly
GB2404953A (en) * 2003-08-15 2005-02-16 Rolls Royce Plc Blade tip clearance system
GB2418955A (en) * 2004-07-09 2006-04-12 United Technologies Corp Blade tip clearance control
GB2418955B (en) * 2004-07-09 2009-07-08 United Technologies Corp Blade clearance control
US7596954B2 (en) 2004-07-09 2009-10-06 United Technologies Corporation Blade clearance control
EP2078822A1 (en) * 2008-01-11 2009-07-15 Snecma Gas-turbine engine with valve for connecting two enclosures
FR2926327A1 (en) * 2008-01-11 2009-07-17 Snecma Sa GAS TURBINE ENGINE WITH TWO SPEAKER COMMUNICATION VALVE
JP2009168022A (en) * 2008-01-11 2009-07-30 Snecma Gas turbine engine provided with valve for establishing communication between two enclosures
US8221061B2 (en) 2008-01-11 2012-07-17 Snecma Gas turbine engine with valve for establishing communication between two enclosures

Also Published As

Publication number Publication date
CH418731A (en) 1966-08-15
DE1286810B (en) 1969-01-09

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