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EP0194957A2 - Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs - Google Patents

Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs Download PDF

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Publication number
EP0194957A2
EP0194957A2 EP86630032A EP86630032A EP0194957A2 EP 0194957 A2 EP0194957 A2 EP 0194957A2 EP 86630032 A EP86630032 A EP 86630032A EP 86630032 A EP86630032 A EP 86630032A EP 0194957 A2 EP0194957 A2 EP 0194957A2
Authority
EP
European Patent Office
Prior art keywords
engine
trench
blades
tips
wall
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.)
Granted
Application number
EP86630032A
Other languages
German (de)
English (en)
Other versions
EP0194957B1 (fr
EP0194957A3 (en
Inventor
Franz Harter
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.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP0194957A2 publication Critical patent/EP0194957A2/fr
Publication of EP0194957A3 publication Critical patent/EP0194957A3/en
Application granted granted Critical
Publication of EP0194957B1 publication Critical patent/EP0194957B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel

Definitions

  • This invention relates to axial flow fans/compressors of gas turbine engines and particularly to the relationship of the tips of the blades to the adjacent shroud or rub strip.
  • the tips of the compressor blades extend adjacent the surrounding shroud or rub strip that is trenched or recessed to the dimension complimentary to the outer station and tip of the blade.
  • the blades which move radially outward during engine acceleration, machine the groove. Obviously, this technique assures a close fit of the mating parts and helps in avoiding leakage around the tips of the blade.
  • a feature of the invention is to provide a slanted trench in the rub strip, shroud, or the engine case of a gas turbine engine adjacent the tips of the blades of the fan and/or compressor.
  • the contour of the blade and the inner wall as seen by the cross section of the trench is angularly disposed relative to the flow path wall.
  • This invention contemplates that the angular contour is designed to effectuate a closure in the gap between the inner wall of the trench and the tip of the blade upon displacement of the compressor and/or fan blade arising out of the growth of the materials resulting from stable speed and temperature operating conditions.
  • the invention in its preferred embodiment is illustrated for use in the lower temperature stations of a gas turbine engine and particularly in the compressor section where a soft material circumscribes the engine's inner diameter of the engine case and is abradable so as to be susceptible of being machined by the operation of the rotating blades.
  • a soft material circumscribes the engine's inner diameter of the engine case and is abradable so as to be susceptible of being machined by the operation of the rotating blades.
  • the blades at zero rotational speeds are spaced from the inner diameter of the rub strip and when accelerated to its highest operating speed, cut into the rub strip to define the trench.
  • the trench shape can be machined out prior to engine operation. What is considered the improvement by the teachings of this invention is the particular contour of the tips of the blades and its cooperating trench.
  • FIG. 1 A portion of a compression section 10 of an axial flow compressor of a gas turbine engine is illustrated in Fig. 1.
  • a flow path 16 for working medium gases extends axially through the compression section.
  • An outer wall 18 having an inwardly facing surface 20 and an inner wall 22 having an outwardly facing surface 24 form the flow path.
  • a plurality of axially spaced rows of rotor blades as represented by the single blades 26 extend outwardly from the rotor across the flow path into proximity with the outer wall.
  • Each blade has an unshrouded tip 28 and is contoured to an airfoil cross section. Accordingly, each blade has a pressure side and a suction side and, as illustrated, has an upstream end 30 and a downstream end 32.
  • Extending over the tips of each row of rotor blades is a stator seal land 34.
  • Each land has a circumferentially extending groove 36 formed therein to a depth D at an inwardly facing surface 37 thereof.
  • a plurality of rows of stator vanes represented by the single vanes 38 are cantilevered inwardly from the stator across the flow path into proximity with the inner wall.
  • Each vane which in this illustration has an unshrouded tip 40, is contoured to an airfoil section. Accordingly, each vane has a pressure side and a suction side and, as illustrated, has an upstream end 42 and a downstream end 44.
  • Extending over the tips of each row of stator vanes is a rotor seal land 46.
  • Each land has a circumferentially extending groove 48 formed therein.
  • the blade tips 26 are spaced from the inwardly facing surface 20.
  • the gap between tips and surface enables assembly of the components.
  • the rotor tips grow radially outward machining the groove 36 in the stator seal land 34.
  • the point of closest proximity of the blades to the bottom of the groove is referred to as the "pinch point * and normally occurs during a transient engine operating to a maximum speed or power condition.
  • the outer wall including the land moves both axially and radially relative to the blade tips to a position at which the blade tips and inner surface 37 define a gap.
  • Fig. 2 which is a prior art design is that the blade 50 penetration into the trench increases with operating speed and causes pumping of air against the trench vertical wall 53 which creates turbulence.
  • the turbulence as shown by arrow A essentially becomes a blockage in the flow path of the gas engine's working medium and adversely affects performance.
  • the maximum depth of blade tip penetration must be controlled to avoid unreasonable turbulence losses at the maximum operating speed. At low speed operating the blade will not penetrate into the trench and leakage can readily occur between the flow path outer wall and the blade tip.
  • the full width of the blade works on the air and has the tendency of over pressurizing this air and hence, creates the undesirable turbulence.
  • the tip of the blade is contoured to be angularly disposed relative to the gas path wall. This is best seen in Fig. 3.
  • the trench is formed to define the contour of the inner surface 37. Looking at the cross section of the trench it is apparent that the axial extension of surface 37 relative to the flow path defined by wall 20 forms angle alpha a. By virtue of this contour, two important features are realized:
  • Fig. 4 exemplifies another configuration on how the tip can be contoured to combat the leakage problem alluded to in the above.
  • the tip of blade 70 is contoured in a sawtooth fashion providing a plurality of parallel channels 72.
  • the inner surface 74 is angularly disposed to the gas path wall providing similar benefits as was described above.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP86630032A 1985-03-11 1986-03-06 Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs Expired - Lifetime EP0194957B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US71027085A 1985-03-11 1985-03-11
US710270 1985-03-11

Publications (3)

Publication Number Publication Date
EP0194957A2 true EP0194957A2 (fr) 1986-09-17
EP0194957A3 EP0194957A3 (en) 1987-06-03
EP0194957B1 EP0194957B1 (fr) 1990-01-31

Family

ID=24853314

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86630032A Expired - Lifetime EP0194957B1 (fr) 1985-03-11 1986-03-06 Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs

Country Status (3)

Country Link
EP (1) EP0194957B1 (fr)
JP (1) JPS61207802A (fr)
DE (2) DE194957T1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0528138A1 (fr) * 1991-08-08 1993-02-24 Asea Brown Boveri Ag Anneau d'aube de turbine axiale
EP0536575A1 (fr) * 1991-10-08 1993-04-14 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
DE19738671A1 (de) * 1997-09-04 1999-03-11 Abb Research Ltd Dichtungsanordnung
EP1840332A1 (fr) * 2006-03-27 2007-10-03 Siemens Aktiengesellschaft Aube de turbomachine et turbomachine
WO2014189564A3 (fr) * 2013-03-06 2015-02-19 United Technologies Corporation Rotor comportant une prétranchée pour turbine à gaz
CN112360816A (zh) * 2020-12-08 2021-02-12 成都成发科能动力工程有限公司 一种轴流压缩机承缸和应用其的轴流压缩机

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6363726A (ja) * 1986-09-05 1988-03-22 Nippon Shokubai Kagaku Kogyo Co Ltd 表面処理用組成物

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH221391A (de) * 1939-04-06 1942-05-31 Maschf Augsburg Nuernberg Ag Spaltabdichtungseinrichtung an den Köpfen der Beschaufelung von Strömungsmaschinen, insbesondere Dampfturbinen.
DE1057137B (de) * 1958-03-07 1959-05-14 Maschf Augsburg Nuernberg Ag Schaufelspaltdichtung bei Kreiselradmaschinen mit deckband- oder deckenscheibenlosenLaufraedern
GB882015A (en) * 1957-04-18 1961-11-08 English Electric Co Ltd Improvements in and relating to high speed axial flow compressors
FR1348186A (fr) * 1963-02-19 1964-01-04 Hélice carénée
CH414681A (de) * 1964-11-24 1966-06-15 Bbc Brown Boveri & Cie Strömungsmaschine
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
GB2034435A (en) * 1978-10-24 1980-06-04 Gerry U Fluid rotary power conversion means
GB2153918A (en) * 1984-02-06 1985-08-29 Gen Electric Compressor casing recess

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH221391A (de) * 1939-04-06 1942-05-31 Maschf Augsburg Nuernberg Ag Spaltabdichtungseinrichtung an den Köpfen der Beschaufelung von Strömungsmaschinen, insbesondere Dampfturbinen.
GB882015A (en) * 1957-04-18 1961-11-08 English Electric Co Ltd Improvements in and relating to high speed axial flow compressors
DE1057137B (de) * 1958-03-07 1959-05-14 Maschf Augsburg Nuernberg Ag Schaufelspaltdichtung bei Kreiselradmaschinen mit deckband- oder deckenscheibenlosenLaufraedern
FR1348186A (fr) * 1963-02-19 1964-01-04 Hélice carénée
CH414681A (de) * 1964-11-24 1966-06-15 Bbc Brown Boveri & Cie Strömungsmaschine
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
GB2034435A (en) * 1978-10-24 1980-06-04 Gerry U Fluid rotary power conversion means
GB2153918A (en) * 1984-02-06 1985-08-29 Gen Electric Compressor casing recess

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0528138A1 (fr) * 1991-08-08 1993-02-24 Asea Brown Boveri Ag Anneau d'aube de turbine axiale
US5238364A (en) * 1991-08-08 1993-08-24 Asea Brown Boveri Ltd. Shroud ring for an axial flow turbine
EP0536575A1 (fr) * 1991-10-08 1993-04-14 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
DE19738671A1 (de) * 1997-09-04 1999-03-11 Abb Research Ltd Dichtungsanordnung
DE19738671B4 (de) * 1997-09-04 2007-03-01 Alstom Dichtungsanordnung
EP1840332A1 (fr) * 2006-03-27 2007-10-03 Siemens Aktiengesellschaft Aube de turbomachine et turbomachine
WO2014189564A3 (fr) * 2013-03-06 2015-02-19 United Technologies Corporation Rotor comportant une prétranchée pour turbine à gaz
US10550699B2 (en) 2013-03-06 2020-02-04 United Technologies Corporation Pretrenched rotor for gas turbine engine
CN112360816A (zh) * 2020-12-08 2021-02-12 成都成发科能动力工程有限公司 一种轴流压缩机承缸和应用其的轴流压缩机

Also Published As

Publication number Publication date
EP0194957B1 (fr) 1990-01-31
DE3668661D1 (de) 1990-03-08
EP0194957A3 (en) 1987-06-03
JPS61207802A (ja) 1986-09-16
DE194957T1 (de) 1987-03-19

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