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
blading
cooling medium
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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
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US415136A
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English (en)
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Buchi Alfred
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-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
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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

  • 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,
  • 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.
  • 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.
  • 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
  • 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.
  • the turbine rotor is designated by I
  • 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.
  • 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.
  • 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.
  • 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.
  • 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,
  • 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.
  • 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
  • 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.
  • the cylindrical base extensions 22 of the buckets are provided with 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.
  • 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.
  • the buckets 6 are directly additionally cooled over all the length thereof and, advantageously, near their entrance portions for the hot gases.
  • 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.
  • 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.
  • 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,
  • 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
  • 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,
US415136A 1940-09-21 1941-10-15 Cooling device for turbine rotors Expired - Lifetime US2364189A (en)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
US2364189A true US2364189A (en) 1944-12-05

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US23172D Expired USRE23172E (en) 1940-09-21 Bochi
US415136A Expired - Lifetime US2364189A (en) 1940-09-21 1941-10-15 Cooling device for turbine rotors

Family Applications Before (1)

Application Number Title Priority Date Filing Date
US23172D Expired USRE23172E (en) 1940-09-21 Bochi

Country Status (7)

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US (2) US2364189A (xx)
BE (1) BE442789A (xx)
CH (1) CH228283A (xx)
DE (1) DE863152C (xx)
FR (1) FR887438A (xx)
GB (1) GB556105A (xx)
NL (1) NL61768C (xx)

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
US2635848A (en) * 1948-10-28 1953-04-21 Packard Motor Car Co Rotor for gas turbines
US2635804A (en) * 1946-12-28 1953-04-21 Int Harvester Co Gas turbine
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 (de) * 1939-09-15 1954-04-12 Bayerische Motoren Werke Ag Luftgekuehltes Abgasturbinenlaufrad
DE952853C (de) * 1942-05-23 1956-11-22 Alfred Buechi Dr Ing Gasturbine mit einer tangential von aussen beaufschlagten, das Treibgas von der radialen Eintritts- in die axiale Austrittsrichtung umlenkenden Laufradscheibe
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 (de) * 1950-05-09 1954-12-31 Maschf Augsburg Nuernberg Ag Verfahren zum Betrieb einer Gasturbinenanlage und Einrichtung zur Durchführung des Verfahrens.
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 (fr) * 1990-05-14 1994-06-10 Alsthom Gec Etage de turbine a action avec pertes secondaires reduites.

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE346599C (xx) *
CH159497A (fr) * 1931-06-09 1933-01-15 Fabrication Des Moteurs Et Tur Dispositif de refroidissement pour roue à aubes d'une turbine à explosions.
CH179552A (de) * 1933-11-25 1935-09-15 Martinka Michael Einrichtung zur Kühlung des Laufrades einer Verbrennungsturbine.
DE665762C (de) * 1936-09-12 1938-10-03 Rheinmetall Borsig Akt Ges Wer Einrichtung zur Kuehlung von Turbinen, insbesondere Gasturbinen
CH205304A (de) * 1937-11-22 1939-06-15 Messerschmitt Boelkow Blohm Verfahren und Einrichtung zum Betrieb einer Gasturbine.
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
US2713990A (en) * 1948-12-21 1955-07-26 Solar Aircraft Co Exhaust structure for gas turbine
US2722101A (en) * 1948-12-21 1955-11-01 Solar Aircraft Co Gas turbine sealing and cooling structure
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
DE863152C (de) 1953-01-15
NL61768C (xx)
CH228283A (de) 1943-08-15
BE442789A (xx)
FR887438A (fr) 1943-11-12
GB556105A (en) 1943-09-21
USRE23172E (en) 1949-11-29

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