US3768924A - Boltless blade and seal retainer - Google Patents

Boltless blade and seal retainer Download PDF

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Publication number
US3768924A
US3768924A US00204992A US3768924DA US3768924A US 3768924 A US3768924 A US 3768924A US 00204992 A US00204992 A US 00204992A US 3768924D A US3768924D A US 3768924DA US 3768924 A US3768924 A US 3768924A
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US
United States
Prior art keywords
rotor
blade
blade retainer
disc
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 - Lifetime
Application number
US00204992A
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English (en)
Inventor
R Andersen
R Corsmeier
J Savage
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General Electric Co
Original Assignee
General Electric Co
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Publication date
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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
    • F01D5/30—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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • ABSTRACT A boltless blade retainer which provides a cooling air chamber around the dovetail slots of a turbomachinery rotor is disclosed to include a continuous annular ring which has a portion extending radially outwardly therefrom to radially position the rotor blades within the dovetail slots and to preclude axial movement of 14 Claims, 3 Drawing Figures f a a. M
  • This invention relates generally to turbomachinery rotor construction and, more particularly, to improved structure for retaining and positioning rotor blades on a turbomachinery rotor disc.
  • the temperature of the hot gas stream which is generated within a combustion section, exceeds the operating temperature capabilities of any practical material from which the turbine vanes and blades could be fabricated.
  • it has become an accepted practice to duct lower temperature, pressurized air from the engines compressor to the turbine components which operate in the hot gas stream environment.
  • the cooling air thus derived is employed in various ways to reduce the metal temperatures of such components. As a general rule, this cooling air is introduced into hollow blades or vanes arid then discharged into the hot gas stream. This cooling air reduces the compo-v nent metal temperatures through various heat transfer mechanisms, such as convective, impingement, or film 5 further helps to form the flow path for delivery of the cooling air to the spacers beneath the blade dovetails.
  • any protrusion from the rotating disc causes wind- 'age within the chamber partially formed by the rotor disc side walls.
  • This windage not only increases the temperature of the air within the chamber but also adds to the overall drag on the turbine rotor, both of which reduce engine performance.
  • the use of bolts causes an additional problem in that bolt holes located within the rotor disc increase the rim loading and result in stress concentration areas.
  • a turbine blade is provided having a thin-walled, cambered airfoil portion, and a single, circular arc dovetail formed integrally therewith.
  • lmpingement inserts extend outwardly from and through radial passageways formed in the dovetail into the cavity of the airfoil portion.
  • the inserts are insertable through this passageway and include a multiplicity of holes directed toward internal surfaces of the airfoil portion.
  • An inlet opening at the bottom end of the insert admits cooling air which is discharged from the insert holes to impinge the airfoil surfaces and cool the same.
  • the impingement inserts are the rotor disc.
  • the turif the spacers could be eliminated, the cost of the turbine rotor assembly would decrease.
  • 'It is desirable, therefore, to provide a blade retainer design which includes provisions for not onlyretaining but also for radially positioning the rotor blades within the dovetail slots and further includes provision for delivery of cooling'air to the blade dovetails without the requirement for a number of bolts extending from either the upstream or downstream sides of the turbine rotor discs.
  • Boltless blade retainers per se are notnew. For example, it is'known to provide mating grooves in a lip extending from the rim of a turbine rotor disc and in the blade dovetails. A locking wire is then positioned within the groove thereby precluding axial movement of the dovetails within the dovetail slots.
  • An example of this type of design is shown "in U.S. Pat. No. 2,713,991 Secord et al. Designs similar to this, however, are concerned merely with precluding axial movement of the blades and not with providing cooling air to the blade nor with connecting a sealing member of any type to the rotor disc.
  • a turbomachinery rotor in which a rotor disc includes a series of equally spaced, hook-shaped fingers near the rim'thereof.
  • a continuous, annular ring blade retainer is designed to include a plurality of tabs which fit between the rotor disc fin gets in an interlocking manner which prevents relative rotation between the blade retainer and the disc.
  • a split retaining ring is installed under the hook-shaped disc fingers, thus securing the blade retainer to the disc.
  • a rabbet is provided near the rim of the rotor disc to support the retainer in the radial direction.
  • FIG. 1 is a fragmentary, generallylongitudinal section through a turbine rotor and blade embodying the present invention
  • FIG. 2 is an enlarged sectional view showing a portion of FIG. 1;
  • FIG. 3 is a fragmentary, axial section taken in the direction of line 3-3 of FIG. 2.
  • a turbine rotor disc 10 is illustrated as having radially projecting turbine blades 12 mounted in a circumferential row thereon.
  • Each blade comprises a cambered airfoil portion 14 which projects into the hot gas stream of the turbine as is well known in the art.
  • a platform 16 is provided at the base of each airfoil portion to compositely blade row.
  • a tang .18 extends inwardly of the platform 16 to attach the blade to the rotor disc 10.
  • the tangs 18 are of the single dovetail, circular arc type and are preferably formed with their opposite sides defined by radii formed from different centers as taught in U.S. Pat. No. 3,378,230, which is of common assignment with the present application.
  • the disc 10 has correspondingly shaped dovetail slots 20 formed across its circumferential face, which slots receive the tangs to mount the blades 12 to the disc 10.
  • the slots 20 have a depth greater than the dovetail height of the tangs 18 to facilitate insertion of the tangs therein and to facilitate delivery of cooling air to the tangs 18 in a manner to be discussed. Since the dovetail slots 20 and the dovetail tangs 18 are not respectively formed on radii swung from a common center, the
  • the space between the bottom of the tangs l8 and the bottom of the dovetail slots20 is generally designated by the numeral 26 (FIGS. 2 and 3) and is supplied with cooling air by means of a plurality of holes 28 formed in the upstream blade retainer 22.
  • the cooling air is delivered to the dovetail slots 20 (or the space 26) from the compressor (not shown) by a passageway '30, which includes a stationary expander nozzle 32 to further cool the air as is well known in the art.
  • Air flows through the expander 32 into a chamber 34 formed by the upstream face of the turbine rotor disc 10, a second rotating disc 36, and the upstream blade retainer 22.
  • the disc 36 is coupled for rotation with thejturbine rotor disc 10 by means of a plurality of bolts 38.
  • the cooling air flows from the expander nozzle 32 into the chamber 34 through a plurality of holes 40 formed within the disc 36. This cooling air then flows from the chamber 34 through the holes 28 in the upstream blade retainer 22an d into the space 26 within the dovetail slots 20. From the slots. 20 the air is delivered .to the I interior portions of the blades 12 in any known manner.
  • the air is deliv eredthrough a plurality of passages 42 formed within the dovetail tangs 18.
  • the passages 42 may be equipped with impingement inserts (not shown) to enhance the cooling capabilities. These inserts could be held in place by a slight interference fit between the insert and the passage 42; and the spacers shown in the Savage et al application could be eliminated, thus further simplifying and reducing the cost of the rotor.
  • the blades 12 are held in their desired radial position withinthe dovetail slots 20 by means of the blade retainers 22 and 24 (thus permitting removal of the spacers).
  • the blade retainers 22 and 24 not only provide this function but also preclude axial movement of the blades 12 within the dovetail slots 20 and, furthermore, provide a sealed cooling air chamber around the dovetail slots and blade tangs, as will now be described.
  • the blade retainer 22 is comprised basically of a continuous, annular ring 44 (FIG.
  • the blade retainer 22 cooperates with the rotor disc 10 and the disc 36 to form the chamber 34.
  • the retainer 22 includes a conical arm 54 which mates with a rim 56 of the disc 36 as shown in FIGS. 1 and 2. If desirable, a suitable seal '58 can be provided between the conical arm 54 and the disc rim, 56.
  • a seal tooth 60 Located between the enlarged head portion 52 and the conical arm 54 of the retainer 22 is a seal tooth 60 which cooperates with a stationary sealing member 62 to prevent leakage of the hot gas stream into a chamber 64 (FIG. 1).
  • the radial leg 46 of the blade retainer 22 includes a plurality of the cooling air holes 28, previously discussed, which permit the delivery of cooling air from the chamber 34 to the spaces 26 within the dovetail slots 20.
  • a second row of cooling air holes 66 can be-positioned radially outwardly from the cooling air holes 28 as shown in FIG. 2 to deliver cooling air from the chamber 64 to the rim of the turbine rotor disc 10.
  • the cooling air holes 66 can be eliminated and any necessary cooling air for the turbine rotor disc rim can be allowed to leak between a projection 68 (FIG. 2), which abuts the, face of the turbine rotor blade shanks,.and the turbine rotor. disc rim.
  • radial slots could be formed in the projection 68 to meter a proper amount of cooling air to the rim area.
  • theprojection 68 provides the basic function of preventing axial movement of the blades 12 within the dovetail slots when the rotor assembly is complete.
  • the ring portion 44 l of the blade retainer 22 fits between the hook-shaped fingers 50 of the turbine rotor disc 10 and a continuous, annular rabbet 70 formed integrally with the rotor disc 10.
  • the rabbet 70 is provided to support the retainer 22 radial load.
  • a split retaining ring 72 is installed between the hookshaped fingers 50 and the tabs 48. In this manner, the retainer 22 is completely secured to the disc 10.
  • the ring 72 is split in at least one location, as shown at 74 (FIG. 3) to permit assembly thereof. When assembled as shown in FIGS. 2 and 3, the ring 72 is captured bent beyondtheir yield points during operation of the rotor disc 10.
  • This overspeed safety stop is provided by holding a close clearance between the inner diameter of the ring portion 44 of the retainer 22 and the outer diameter of the fingers at location 80 (FIG. 2). Critical loads which would otherwise occur in the fingers 50 are thus transferred directly to the rabbets 70 of the disc '10. l
  • the retainer tabs 48 are indexed between the disc fingers 50.
  • the retainers are pushed axially onto-the disc until projection 68 contacts the disc 10.
  • a simple installation tool is then used to push the tabs 48 toward the rotor disc 10.
  • the split ring 72 is then positionedbetween the fingers 50 and the tabs 48, and the tabs 48 are permitted to return to their normal position thus securing the ring 72 as described above.
  • a shoulder 84 is formed integrally with the tabs 48 to preclude the tabs48 from being bent beyond their yield points during assembly.
  • the rotor blades 12 are positioned within the dovetail slot 20 and the blade retainer 24 is then assembled on the opposite side of the rotor disc 10 in a manner similar to that described above for the blade retainer 22. Disassembly of the rotor is accomplished by merely reversing the above-described steps. Shoulders 82 and 83 are provided for pulling the retainers off the disc.
  • the blade retainers 22 and 24 secure theblades 12 in their desired radial positions and preclude axial movement of the blades 12 within the dovetail slots 20.
  • the blade retainers 22 and 24 provide a sealed chamber around the bottom of the dovetail slots for the delivery of cooling air thereto in the manner described above.
  • This sealed chamberv is provided by. the close fit between the projecting portions 68 of the retainers and the rim of the rotor disc 10 and, furthermore, by the continuousseal between the ring portion 44 and the rabbets 70.
  • a boltless blade retainer for a turbomachinery rotor which includes a rotor disc having a plurality of blade dovetail slots therein and a plurality of rotor blades positioned within the slots, said blade retainer comprising:
  • leg extending radially outwardly from said ring, said leg including means for radially positioning the rotor blades within the dovetail slots and means for preventing axial movement of the rotor blades within the slots, and
  • said leg defining a cooling air chamber around at least a portion of the dovetail slots of the rotor disc.
  • hook-shaped fingers include a first portion extending axially from the face of said disc and a second portion extending radially inwardly from said first portion, said combination further including a locking strip positioned between said tabs and said second portion of said fingers.
  • a combination as recited in claim 6 further including a plurality of rotor blades positioned within the dovetail slots, said blades including platforms forming the inner bounds of a gas flow passage, said blade retainers being further characterized in that said means for radially positioning said blades comprise an enlarged head portion at the top of said blade retainer leg, and said head portion lies beneath and supports said blade platforms.
  • a turbomachinery rotor which includes at least one rotor disc having a plurality ofblade dovetail slots located in the rim thereof, a rotor blade positioned within each of said blade dovetail slots, and a boltless blade retainer, said blade retainercomprising:
  • leg extending radially outwardly from said ring, said leg including means for radially positioning said rotor blades within said dovetail slots and means for preventing axial movement of said rotor blades within said slots, and
  • said leg defining a cooling air chamber around at least a portion of said dovetail slots of said rotor disc.
  • a turbomachinery rotor as recited in claim 11 including a second blade retainer, said first blade retainer being secured to a first face of said rotor disc and said second blade retainer being secured to the opposite face of said rotor disc.
  • leg extending radially outwardly from said ring, said leg including means for radially positioning the rotor blades within the dovetail slots and means for preventing axial movement ofthe rotor blades within the slots, and
  • said leg defining a cooling air chamber around at least a portion of the dovetail slots of the rotor disc.
  • a turbomachinery rotor as recited in claim 12 including a first locking strip positioned between said blade retainer tabs and said hooked-shaped fingers of said first face, and a second locking strip positioned between said blade retainer tabs of said second blade retainer and hook-shaped fingers formed integrally with and extending from said opposite face of said rotor disc.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00204992A 1971-12-06 1971-12-06 Boltless blade and seal retainer Expired - Lifetime US3768924A (en)

Applications Claiming Priority (1)

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US20499271A 1971-12-06 1971-12-06

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US3768924A true US3768924A (en) 1973-10-30

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US00204992A Expired - Lifetime US3768924A (en) 1971-12-06 1971-12-06 Boltless blade and seal retainer

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US (1) US3768924A (enrdf_load_stackoverflow)
JP (1) JPS5531281B2 (enrdf_load_stackoverflow)
BE (1) BE792286A (enrdf_load_stackoverflow)
CA (1) CA982483A (enrdf_load_stackoverflow)
DE (1) DE2258618C2 (enrdf_load_stackoverflow)
FR (1) FR2164197A5 (enrdf_load_stackoverflow)
GB (1) GB1410658A (enrdf_load_stackoverflow)
IL (1) IL40583A0 (enrdf_load_stackoverflow)

Cited By (51)

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US4086757A (en) * 1976-10-06 1978-05-02 Caterpillar Tractor Co. Gas turbine cooling system
DE2842095A1 (de) * 1977-12-28 1979-07-12 Gen Electric Vorrichtung zum festhalten von schaufeln an einem rotor
US4192633A (en) * 1977-12-28 1980-03-11 General Electric Company Counterweighted blade damper
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
US4309145A (en) * 1978-10-30 1982-01-05 General Electric Company Cooling air seal
US4359789A (en) * 1972-01-31 1982-11-23 Monogram Industries, Inc. Sewerless disposal system
US4480959A (en) * 1982-03-12 1984-11-06 S.N.E.C.M.A. Device for damping vibrations of mobile turbine blades
US4480958A (en) * 1983-02-09 1984-11-06 The United States Of America As Represented By The Secretary Of The Air Force High pressure turbine rotor two-piece blade retainer
US4507052A (en) * 1983-03-31 1985-03-26 General Motors Corporation End seal for turbine blade bases
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
US4701105A (en) * 1986-03-10 1987-10-20 United Technologies Corporation Anti-rotation feature for a turbine rotor faceplate
US4836750A (en) * 1988-06-15 1989-06-06 Pratt & Whitney Canada Inc. Rotor assembly
US4890981A (en) * 1988-12-30 1990-01-02 General Electric Company Boltless rotor blade retainer
US5030063A (en) * 1990-02-08 1991-07-09 General Motors Corporation Turbomachine rotor
US5281098A (en) * 1992-10-28 1994-01-25 General Electric Company Single ring blade retaining assembly
US5353587A (en) * 1992-06-12 1994-10-11 General Electric Company Film cooling starter geometry for combustor lines
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
DE3310529A1 (de) * 1982-03-23 1996-10-31 Snecma Vorrichtung zum Kühlen des Rotors einer Gasturbine
US5622475A (en) * 1994-08-30 1997-04-22 General Electric Company Double rabbet rotor blade retention assembly
US5630703A (en) * 1995-12-15 1997-05-20 General Electric Company Rotor disk post cooling system
US5713385A (en) * 1996-11-18 1998-02-03 Traylor; Paul L. Air gap body for reverse osmosis system
US5800124A (en) * 1996-04-12 1998-09-01 United Technologies Corporation Cooled rotor assembly for a turbine engine
US6095750A (en) * 1998-12-21 2000-08-01 General Electric Company Turbine nozzle assembly
EP0926314A4 (en) * 1997-06-18 2001-01-24 Mitsubishi Heavy Ind Ltd SEALING STRUCTURE FOR GAS TURBINES
US6520743B2 (en) * 2000-08-10 2003-02-18 Snecma Moteurs Rotor blade retaining apparatus
US20040062643A1 (en) * 2002-09-30 2004-04-01 General Electric Company Turbomachinery blade retention system
EP1571294A1 (fr) 2004-03-03 2005-09-07 Snecma Moteurs Flasque-crochet annulaire pour un disque de rotor
US20050201857A1 (en) * 2004-03-13 2005-09-15 Rolls-Royce Plc Mounting arrangement for turbine blades
US6951448B2 (en) 2002-04-16 2005-10-04 United Technologies Corporation Axial retention system and components thereof for a bladed rotor
US20070014668A1 (en) * 2005-07-18 2007-01-18 Siemens Westinghouse Power Corporation Seal and locking plate for turbine rotor assembly between turbine blade and turbine vane
US20070020089A1 (en) * 2005-07-21 2007-01-25 Snecma A device for damping vibration of a ring for axially retaining turbomachine fan blades
JP2010001841A (ja) * 2008-06-20 2010-01-07 Mitsubishi Heavy Ind Ltd 動翼およびガスタービン
US20100232939A1 (en) * 2009-03-12 2010-09-16 General Electric Company Machine Seal Assembly
US20100232938A1 (en) * 2009-03-12 2010-09-16 General Electric Company Gas Turbine Having Seal Assembly with Coverplate and Seal
US8425194B2 (en) 2007-07-19 2013-04-23 General Electric Company Clamped plate seal
CN101333938B (zh) * 2007-06-27 2013-06-19 斯奈克玛 一种采用两路供气冷却涡轮机转子盘叶根安装槽的装置
US8469656B1 (en) 2008-01-15 2013-06-25 Siemens Energy, Inc. Airfoil seal system for gas turbine engine
US20140193272A1 (en) * 2013-01-08 2014-07-10 General Electric Company Gas Turbine Engine Cooling Systems and Methods Incorporating One or More Cover Plate Assemblies Having One or More Apertures Therein
US8776347B2 (en) 2012-06-29 2014-07-15 United Technologies Corporation Tool for rotor assembly and disassembly
US20140271150A1 (en) * 2012-07-18 2014-09-18 Snecma Labyrinth disk for a turbomachine
US8870544B2 (en) 2010-07-29 2014-10-28 United Technologies Corporation Rotor cover plate retention method
US9109450B2 (en) 2012-06-14 2015-08-18 United Technologies Corporation Rotor assembly with interlocking tabs
US9145771B2 (en) 2010-07-28 2015-09-29 United Technologies Corporation Rotor assembly disk spacer for a gas turbine engine
US20160153302A1 (en) * 2014-12-01 2016-06-02 General Electric Company Turbine wheel cover-plate mounted gas turbine interstage seal
US20160222787A1 (en) * 2013-10-03 2016-08-04 United Technologies Corporation Feature to provide cooling flow to disk
CN106567749A (zh) * 2015-08-14 2017-04-19 安萨尔多能源瑞士股份公司 燃气涡轮冷却系统和方法
US20170298739A1 (en) * 2016-04-15 2017-10-19 Siemens Energy, Inc. Bolt On Seal Ring
US20170328226A1 (en) * 2014-11-27 2017-11-16 Hanwha Techwin Co., Ltd. Turbine apparatus
EP3102793A4 (en) * 2014-01-24 2017-12-06 United Technologies Corporation Toggle seal for a rim seal
US10018063B2 (en) * 2015-06-10 2018-07-10 United Technologies Corporation Anti-rotation knife edge seals and gas turbine engines including the same
US20250043799A1 (en) * 2023-08-04 2025-02-06 Rtx Corporation Control of leakage for gas turbine engine compressor blades

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FR2710103B1 (fr) * 1993-09-16 1995-10-20 Snecma Flasque de rotor de turbomachine et assemblage de ce flasque avec un rotor.
US5984636A (en) * 1997-12-17 1999-11-16 Pratt & Whitney Canada Inc. Cooling arrangement for turbine rotor
JP2005009382A (ja) * 2003-06-18 2005-01-13 Ishikawajima Harima Heavy Ind Co Ltd タービンロータ、タービンディスク、及びタービン

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Cited By (75)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4359789A (en) * 1972-01-31 1982-11-23 Monogram Industries, Inc. Sewerless disposal system
US4086757A (en) * 1976-10-06 1978-05-02 Caterpillar Tractor Co. Gas turbine cooling system
DE2842095A1 (de) * 1977-12-28 1979-07-12 Gen Electric Vorrichtung zum festhalten von schaufeln an einem rotor
FR2413543A1 (fr) * 1977-12-28 1979-07-27 Gen Electric Dispositif de retenue d'aubes de turbomachine
US4192633A (en) * 1977-12-28 1980-03-11 General Electric Company Counterweighted blade damper
US4309145A (en) * 1978-10-30 1982-01-05 General Electric Company Cooling air seal
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
DE3124250A1 (de) * 1980-06-23 1982-06-03 General Electric Co., Schenectady, N.Y. "vorrichtung und verfahren zum befestigen eines teils an einem gebilde"
US4480959A (en) * 1982-03-12 1984-11-06 S.N.E.C.M.A. Device for damping vibrations of mobile turbine blades
DE3310529A1 (de) * 1982-03-23 1996-10-31 Snecma Vorrichtung zum Kühlen des Rotors einer Gasturbine
DE3310529C2 (de) * 1982-03-23 1998-10-08 Snecma Vorrichtung zum Kühlen des Rotors einer Gasturbine
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Also Published As

Publication number Publication date
JPS5531281B2 (enrdf_load_stackoverflow) 1980-08-16
IL40583A0 (en) 1972-12-29
CA982483A (en) 1976-01-27
JPS4865506A (enrdf_load_stackoverflow) 1973-09-10
BE792286A (fr) 1973-03-30
DE2258618A1 (de) 1973-06-07
DE2258618C2 (de) 1983-10-20
GB1410658A (en) 1975-10-22
FR2164197A5 (enrdf_load_stackoverflow) 1973-07-27

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