US2364189A - Cooling device for turbine rotors - Google Patents

Cooling device for turbine rotors Download PDF

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Publication number
US2364189A
US2364189A US415136A US41513641A US2364189A US 2364189 A US2364189 A US 2364189A US 415136 A US415136 A US 415136A US 41513641 A US41513641 A US 41513641A US 2364189 A US2364189 A US 2364189A
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United States
Prior art keywords
turbine
rotor
cooling
cooling medium
blading
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Expired - Lifetime
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US415136A
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Buchi Alfred
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Buchi Alfred
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Priority to CH556105X priority Critical
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08Cooling; Heating; Heat-insulation
    • F01D25/12Cooling
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02Blade-carrying members, e.g. rotors
    • F01D5/08Heating, heat-insulating or cooling means
    • F01D5/081Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies
    • Y02T50/67Relevant aircraft propulsion technologies
    • Y02T50/673Improving the blades aerodynamics
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies
    • Y02T50/67Relevant aircraft propulsion technologies
    • Y02T50/675Enabling an increased combustion temperature by cooling
    • Y02T50/676Blades cooling

Description

Dec. 5, 1944. A. BUCHI 2,364,189

COOLING DEVICE FOR TURBINE ROTORS Filed Oct. 15, 1941 2 she ets-sheet l T M J J 5 a 7 4 3+ a lnvenfw? Dec. 5, 1944. A. BUCHI 2,364,189

COOLING DEVICE FOR TURBINE ROTORS Filed Oct. 15, 1941 2 Sheets-Sheet 2 Patented Dec. 5, 1944 UNITED STATES PATENT OFFICE 7 2,364,189 COOLING DEVICE FOR TURBINE ROTORS Alfred Biichl, Winterthm', Switzerland Application October 15, 1941, Serial No. 415,136

In Switzerland September 21, 1940 3 Claims.

parts inherent energy to the turbine buckets and is passed from the inlet to the exit side of the turbine bucket arrangement at the region of the I base portions of the buckets. However, part of the delivery of the cooling fan means may be blown through passages disposed adjacent to the point of connection of the turbine buckets with the turbine rotor, by which provision the bucket connecting means are additionally cooled and heat conduction towards the body of the turbine rotor is prevented.

The turbine rotor may-be provided with fan blading only on that of its end faces adjacent the inlet side of the turbine for the power fluid,

or on both end faces. Exteriorly beyond the cooling fan blading diffuser or guide vanes may be arranged in the stationary part of the turbine casing surrounding the turbine rotor, for conveying the cooling means towards the bucket arrangement of the turbine. For the purpose of obtaining effective transmission of heat from the turbine rotor to the cooling means the fan blades are made integral with the turbine rotor. The fan blading employed may be of any suitable type and the disposition of the blading may be chosen to suit requirements.

The bearing arrangement of the turbine rotor may be such that the rotor projects freely therefrom with one rotor end face unobstructed so that cooling air can be directly guided towards the cooling fan blading from without unimpeded.

In the accompanying drawings embodiments of the invention are illustrated by way of example only, in which Fig. 1 is a sectional view of a single-stage turbine driven'blower, cooling fan bladings being Ill) arranged on both end faces of the turbine rotor;

Figs. 2, 3 and 4 show details of means for the guidance of the cooling medium delivery of the cooling fan, and

Fig. 5 shows a section of a single-stage gas turbine driven blower provided with cooling fan blading only on the end face of the turbine rotor situated at the inlet side of the turbine for the power fluid.

In Fig. 1, the turbine rotor is designated by I, whereas the numeral 2 denotes the blower rotor driven by the turbine rotor. A two-part cooled turbine casing 3 surrounds the blower rotor. The numerals 4 and 5 refer to the gas supply conduits leading into the turbine and the nozzlering respectively, the gases being projected onto the bucket arrangement 6 of the turbine rotor I through said ring. The intake of the blower is designated by I, and 8 refers to the diffuser casing of the blower. The turbine rotor I has its bearings 8, I0 in a bearing sleeve I2 inside of a stationary bearing support I within the blower casing, and the blower rotor 2 is connected to the turbine rotor I by a sleeve-like extension I3.

The invention is concerned with the cooling fan bladings I4 and I4 arranged on either end face of the turbine rotor I, as shown in. Fig. 1. By the action of the bladings I4, I4 the cooling medium, which may be air or the like, is sucked in in the region of the hub portion of the blower rotor, and is conveyed towards the outer end face of the turbine rotor. During the passage of the air through the bladings I4 and/or I4 this air first cools the bucket wheel disc I and keeps on cooling in this way until it leaves the blading I4 or I4 respectively. Thereupon the cooling air, when leaving the blading II, is deflected by the stationary diffuser blading I5 into the rotating bucket arrangement 6 of the turbine rotor I, so that a film of cold air is blown through the bucket arrangement in between the hot power gases, which pass through the turbine bucket arrangement 6 at a point disposed radially further outward, and the base extensions I9 of the buckets. By this means not only the end walls of the turbine rotor, the base extensions I9 and the inner portions I8 of the buckets are cooled, but the heat flux passing from the hot gases conveyed through the outermost portions of the buckets 6 towards the body of the rotor I is considerably reduced at the same time and theradially outer bucket portions are also cooled. Cooling air is suplied from without at the inlet side of the turbine through the supply funnel I6, if, as shown in Fig. 1, a freely projecting turbine wheel with an unobstructed outer end faceis used.

The air drawn in and delivered by the cooling fan blading I4 is supplied to the latter from without through bores 25. The numeral l5 refers ,to cooling air difluser blades being, for example,

arranged exteriorly of the fan rotor in the stationary part of'the turbine, and, if desired, sunk in the material of said part. The diffuser blades l deflect the air delivered by the blading It to the right in Fig. 1 into the inner portion of the turbine buckets 6, advantageously, at such an angle that in addition to producing a cooling effect this air imparts inherent energy thereof to the turbine rotor I. In order to provide for deflecting the cooling air with as little loss of energy as possible on the turbine rotor l at a point radially beyond the cooling fan blading II a .thickened portion l'l aerodynamically improving f iethe deflecting of the cooling medium into the 'difluser blades l5 may be arranged on one or both end faces of said rotor.

Fig. 2 is a view of a segment of the turbine bucket arrangement on a larger scale showing the path along which the cooling air flows through the turbine bucket arrangement 6. The radially inner portions 18 of the turbine bucket arrangement 6 are cooled by the air passing out of the diffuser blading l5 for the cooling air. The base extensions IQ of the turbine buckets 6 are so shaped that adjacent to the joints 2| between the individual buckets and, upon choice,

also in the adjoining portions of the turbinerotor I, passages 20 are formed throughwhich at least part of the air output of the cooling fan is conveyed towards the exit side of the turbine buckets 6. By this means the base extensions l9 and the radially outer portions of the turbine rotor I are cooled. In order that the turbine bucket arrangement 6 is, nevertheless, firmly secured to the turbine rotor l the arrangement is so chosen that adjacent turbine buckets touch each other on the outside of the surfaces 2|.

In an arrangement of the base portions 19 as shown in Fig. 2, for example, also the cylindrical base extensions 22 of the buckets are provided with passages 23. Through the passages 23 a further portion of the air delivered by the cooling fan will pass and thus additionally cool the base extensions 19 directly, whereby the turbine rotor l is cooled indirectly, in addition. By virtue of the cooling thus provided not only the temperature of the turbine rotor and that of the base extensions is brought down and, consequently. greater strength of material is obtained for these parts even at high temperatures of the power gas,

but also reduced straining due to expansion by heat of the parts fitted together results, and improved resistivity of the assembly at the same time.

Alternatively, part of the cooling air at least may, as also shown in Fig. 2, be passed through bores 26 provided in the turbine buckets 6 which bores receive, for example, the cooling air leaving the passages 20, or other cooling air. By this means the buckets 6 are directly additionally cooled over all the length thereof and, advantageously, near their entrance portions for the hot gases.

In Fig. 3 the cooling fan blades, which are designated by l4, are preferably in the form of radial blades for reasons of strength. This blade arrangement ensures minimum straining of the turbine rotor and, if made integrally with the turbine rotor I, maximum heat transmission from the rotor to the cooling medium is ensured at the same time. By the flow of air passing through between the blades l4 and It the turbine rotor is satisfactorily cooled.

In Fig. 4 the stationary difl'user blade arrangement ii for deflecting the cooling air into the blower having a cooling fan blading ll only on the end face of the rotor l adjacent the gas inlet side of the turbine.

I The invention can be applied also to turbines into which the power fluid is introduced in various other directions of flow, and may further be applied to individual rotors or all the rotors of multi-stage turbines. The invention has the great advantage that a considerable proportion of the energy consumed for the conveyance of the cooling medium is recovered and any substantial losses. due to change of direction of flow are avoided.

Owing to the temperature of the cooling medium rising already while the latter cools the turbine rotor disc, the gathering up of heat by said medium is more effective than if the cooling medium would be conducted into the turbine bucket arrangement directly from outside without being preheated.

I claim:

1. In a cooling device for turbine rotors for hot power fluids, a turbine rotor having a disc-shaped wheel body. a bucket arrangement disposed on said wheel body, cooling fan blading means provided on said wheel body in driving association with said rotorfor delivering a cooling medium, a casing forsaid rotor including ide walls, the wall on the inlet side of the turbine providing conduction means for said cooling medium, delivered by said fan blading means for directing the cooling medium outwardly, sweeping and thus cooling said wheel body and then changing the direction of flow of the cooling medium at the periphery of the wheel body so as to pass axially across the rotor periphery to form a cooling and insulating layer to 'cool and protect the roots of the buckets and the rotor body from hot gases,

2. In a cooling device for turbine rotors for hot power fluids, a turbine rotor having a disc-shaped wheel body, a bucket arrangement disposed on said wheel body, cooling fan blading means provided on said wheel body in driving association with said rotor for delivering a cooling medium, a casing for said rotor including side walls, the wall on the inlet side of the turbine providing conduction means for said cooling medium, delivered by said fan blading means for directing the cooling medium outwardly, sweeping and thus cooling said wheel body and then changing the direction of flow of the cooling medium at the periphery of the wheel body so as to pass axially across the rotor periphery to form a cooling and insulating layer to cool and protect the roots of the buckets and the rotor body from hot gases, forwardly inclined vanes arranged in the conduction means of the casing exteriorly beyond said cooling fan blading means immediately adjacent the rotor body for guiding said cooling medium towards said bucket arrangement and in the direction of movement thereof, and thickenings disposed on an unobstructed end face of said rotor, in advance of sold inclined vanesas regards the flow or said cooling medium, for aerodynamically improving the passage of said flow into said inclined vanes.

3. In a cooling device for turbine rotors for hot power fluids, a turbine rotor having a disc-shaped wheel body, a bucket arrangement disposed on said wheel body, cooling fan blading means provided on said wheel body in driving association with said rotor for delivering 'a cooling medium, a casing for said rotor including side walls, the wall on the inlet side of the turbine providing conduction means for said cooling medium, delivered by said fan blading means for directing the cooling medium outwardly, sweeping and thus cooling said wheel body and then changing the direction of flow of the cooling medium at the periphery oi the wheel body so as to pass axially across the rotor periphery to form a cooling and insulating layer to cool and protect the roots of the buckets and the rotor body from hot gases, forwardly inclined flow-directing vanes arranged in the conduction means 01' the casing exteriorly beyond said cooling fan blading means immediately adjacent the rotor body for guiding said cooling medium in the direction of movement of said bucket arrangement, and thickenings disposed on both end faces of said rotor radially outwardly of said fan blading means in op;- position to the cooling medium inlet end of said vanes, for aerodynamically improving the flow of cooling medium toward the turbine exit. V

ALFRED BUCHI.

US415136A 1940-09-21 1941-10-15 Cooling device for turbine rotors Expired - Lifetime US2364189A (en)

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Application Number Priority Date Filing Date Title
CH556105X 1940-09-21

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US415136A Expired - Lifetime US2364189A (en) 1940-09-21 1941-10-15 Cooling device for turbine rotors

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BE (1) BE442789A (en)
CH (1) CH228283A (en)
DE (1) DE863152C (en)
FR (1) FR887438A (en)
GB (1) GB556105A (en)
NL (1) NL61768C (en)

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2434134A (en) * 1939-12-19 1948-01-06 Power Jets Res & Dev Ltd Cooling means for internal-combustion turbine wheels of jet propulsion engines
US2459935A (en) * 1941-11-21 1949-01-25 Dehavilland Aircraft Jet propulsion plant
US2468461A (en) * 1943-05-22 1949-04-26 Lockheed Aircraft Corp Nozzle ring construction for turbopower plants
US2484275A (en) * 1947-09-19 1949-10-11 United Specialties Co Supercharger seal
US2577179A (en) * 1942-08-18 1951-12-04 Buchi Alfred Cooling device for radial gas turbines
US2614386A (en) * 1945-02-20 1952-10-21 Power Jets Res & Dev Ltd Supporting and reinforcing structure for gas turbine engines
US2620123A (en) * 1946-05-31 1952-12-02 Continental Aviat & Engineerin Cooling system for combustion gas turbines
US2625366A (en) * 1948-11-18 1953-01-13 Packard Motor Car Co Turbine rotor construction
US2626502A (en) * 1947-05-29 1953-01-27 Lagelbauer Ernest Cooling system for gas turbine blading
US2635849A (en) * 1946-08-13 1953-04-21 Buchi Alfred Turbine stage
US2635804A (en) * 1946-12-28 1953-04-21 Int Harvester Co Gas turbine
US2635848A (en) * 1948-10-28 1953-04-21 Packard Motor Car Co Rotor for gas turbines
US2684196A (en) * 1949-09-17 1954-07-20 Garrett Corp Turbine driven fan unit
US2684831A (en) * 1947-11-28 1954-07-27 Power Jets Res & Dev Ltd Turbine and like rotor
US2700530A (en) * 1948-08-27 1955-01-25 Chrysler Corp High temperature elastic fluid apparatus
US2700935A (en) * 1948-04-27 1955-02-01 Bendix Aviat Corp Rocket fuel pump and the like
US2713990A (en) * 1948-12-21 1955-07-26 Solar Aircraft Co Exhaust structure for gas turbine
US2717118A (en) * 1952-03-07 1955-09-06 Worthington Corp Turbo-compressor
US2722101A (en) * 1948-12-21 1955-11-01 Solar Aircraft Co Gas turbine sealing and cooling structure
US2752856A (en) * 1951-02-01 1956-07-03 Bendix Aviat Corp Turbine pump assembly
US2777632A (en) * 1953-04-07 1957-01-15 American Motors Corp Supercharger for internal combustion engines
US2783965A (en) * 1949-02-01 1957-03-05 Birmann Rudolph Turbines
US2801518A (en) * 1952-09-17 1957-08-06 Solar Aircraft Co Gas turbine
US2823516A (en) * 1951-10-30 1958-02-18 Garrett Corp Ducted fan power plant for aircraft
US2888302A (en) * 1955-09-19 1959-05-26 Garrett Corp Turbine driven fluid circulating unit
US2916258A (en) * 1956-10-19 1959-12-08 Gen Electric Vibration damping
US3009682A (en) * 1951-05-16 1961-11-21 Power Jets Res & Dev Ltd Gas turbines
US3051438A (en) * 1957-02-22 1962-08-28 Rolls Royce Axial-flow blading with internal fluid passages
US4093399A (en) * 1976-12-01 1978-06-06 Electric Power Research Institute, Inc. Turbine rotor with ceramic blades
US20120020789A1 (en) * 2009-04-02 2012-01-26 Turbomeca Turbine wheel having de-tuned blades and including a damper device

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE909059C (en) * 1939-09-15 1954-04-12 Bayerische Motoren Werke Ag Luftgekuehltes exhaust turbine impeller
DE952853C (en) * 1942-05-23 1956-11-22 Alfred Buechi Dr Ing Gas turbine with a tangential acted upon from the outside, the propellant gas from the radial inlet in the axial outlet direction deflecting rotor disk
US2647368A (en) * 1949-05-09 1953-08-04 Hermann Oestrich Method and apparatus for internally cooling gas turbine blades with air, fuel, and water
CH304143A (en) * 1950-05-09 1954-12-31 Maschf Augsburg Nuernberg Ag A method of operating a gas turbine plant and means for performing the method.
US2795371A (en) * 1952-04-28 1957-06-11 Sr Alfred Buchi Overhung supported turbo-blower rotors
US2891382A (en) * 1952-07-29 1959-06-23 Gen Motors Corp Liquid-cooled turbine
US2858102A (en) * 1954-09-03 1958-10-28 Gen Electric Turbomachine wheels and methods of making the same
US2956772A (en) * 1955-08-19 1960-10-18 John C Freche Liquid-spray cooling method
US2922569A (en) * 1956-04-14 1960-01-26 Alfred J Buchi Means for lubricating and cooling a turbine-driven compressor
US2974925A (en) * 1957-02-11 1961-03-14 John C Freche External liquid-spray cooling of turbine blades
US3230710A (en) * 1962-12-24 1966-01-25 Garrett Corp Gas turbine
US3981143A (en) * 1974-08-15 1976-09-21 The United States Of America As Represented By The Secretary Of The Army Infrared suppressor
FR2661946B1 (en) * 1990-05-14 1994-06-10 Alsthom Gec Turbine stage action with a secondary losses reduced.

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE346599C (en) *
CH159497A (en) * 1931-06-09 1933-01-15 Fabrication Des Moteurs Et Tur wheel for cooling device explosions blades of a turbine.
CH179552A (en) * 1933-11-25 1935-09-15 Martinka Michael Means for cooling the impeller of a combustion turbine.
DE665762C (en) * 1936-09-12 1938-10-03 Rheinmetall Borsig Ag Device for Cooling of turbines, particularly gas turbines
CH205304A (en) * 1937-11-22 1939-06-15 Messerschmitt Boelkow Blohm Method and device for operating a gas turbine.
GB504781A (en) * 1937-12-09 1939-05-01 Bayerische Motoren Werke Ag Device for cooling exhaust gas turbines and their casings

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2434134A (en) * 1939-12-19 1948-01-06 Power Jets Res & Dev Ltd Cooling means for internal-combustion turbine wheels of jet propulsion engines
US2459935A (en) * 1941-11-21 1949-01-25 Dehavilland Aircraft Jet propulsion plant
US2577179A (en) * 1942-08-18 1951-12-04 Buchi Alfred Cooling device for radial gas turbines
US2468461A (en) * 1943-05-22 1949-04-26 Lockheed Aircraft Corp Nozzle ring construction for turbopower plants
US2614386A (en) * 1945-02-20 1952-10-21 Power Jets Res & Dev Ltd Supporting and reinforcing structure for gas turbine engines
US2620123A (en) * 1946-05-31 1952-12-02 Continental Aviat & Engineerin Cooling system for combustion gas turbines
US2635849A (en) * 1946-08-13 1953-04-21 Buchi Alfred Turbine stage
US2635804A (en) * 1946-12-28 1953-04-21 Int Harvester Co Gas turbine
US2626502A (en) * 1947-05-29 1953-01-27 Lagelbauer Ernest Cooling system for gas turbine blading
US2484275A (en) * 1947-09-19 1949-10-11 United Specialties Co Supercharger seal
US2684831A (en) * 1947-11-28 1954-07-27 Power Jets Res & Dev Ltd Turbine and like rotor
US2700935A (en) * 1948-04-27 1955-02-01 Bendix Aviat Corp Rocket fuel pump and the like
US2700530A (en) * 1948-08-27 1955-01-25 Chrysler Corp High temperature elastic fluid apparatus
US2635848A (en) * 1948-10-28 1953-04-21 Packard Motor Car Co Rotor for gas turbines
US2625366A (en) * 1948-11-18 1953-01-13 Packard Motor Car Co Turbine rotor construction
US2722101A (en) * 1948-12-21 1955-11-01 Solar Aircraft Co Gas turbine sealing and cooling structure
US2713990A (en) * 1948-12-21 1955-07-26 Solar Aircraft Co Exhaust structure for gas turbine
US2783965A (en) * 1949-02-01 1957-03-05 Birmann Rudolph Turbines
US2684196A (en) * 1949-09-17 1954-07-20 Garrett Corp Turbine driven fan unit
US2752856A (en) * 1951-02-01 1956-07-03 Bendix Aviat Corp Turbine pump assembly
US3009682A (en) * 1951-05-16 1961-11-21 Power Jets Res & Dev Ltd Gas turbines
US2823516A (en) * 1951-10-30 1958-02-18 Garrett Corp Ducted fan power plant for aircraft
US2717118A (en) * 1952-03-07 1955-09-06 Worthington Corp Turbo-compressor
US2801518A (en) * 1952-09-17 1957-08-06 Solar Aircraft Co Gas turbine
US2777632A (en) * 1953-04-07 1957-01-15 American Motors Corp Supercharger for internal combustion engines
US2888302A (en) * 1955-09-19 1959-05-26 Garrett Corp Turbine driven fluid circulating unit
US2916258A (en) * 1956-10-19 1959-12-08 Gen Electric Vibration damping
US3051438A (en) * 1957-02-22 1962-08-28 Rolls Royce Axial-flow blading with internal fluid passages
US4093399A (en) * 1976-12-01 1978-06-06 Electric Power Research Institute, Inc. Turbine rotor with ceramic blades
US20120020789A1 (en) * 2009-04-02 2012-01-26 Turbomeca Turbine wheel having de-tuned blades and including a damper device
US8876472B2 (en) * 2009-04-02 2014-11-04 Turbomeca Turbine wheel having de-tuned blades and including a damper device

Also Published As

Publication number Publication date
USRE23172E (en) 1949-11-29
NL61768C (en)
BE442789A (en)
GB556105A (en) 1943-09-21
CH228283A (en) 1943-08-15
FR887438A (en) 1943-11-12
DE863152C (en) 1953-01-15

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