GB825967A - Improvements in turbines and in particular gas turbines - Google Patents

Improvements in turbines and in particular gas turbines

Info

Publication number
GB825967A
GB825967A GB9772/57A GB977257A GB825967A GB 825967 A GB825967 A GB 825967A GB 9772/57 A GB9772/57 A GB 9772/57A GB 977257 A GB977257 A GB 977257A GB 825967 A GB825967 A GB 825967A
Authority
GB
United Kingdom
Prior art keywords
blade
working fluid
fluid
blades
under pressure
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
GB9772/57A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB825967A publication Critical patent/GB825967A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • 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
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film 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
    • F01D5/12—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
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F16J15/42—Sealings between relatively-moving surfaces by means of fluid kept in sealing position by centrifugal force
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Abstract

825,967. Turbine blades; cooling gas turbines. POUIT, R. J. March 25, 1957 [March 28, 1956; July 10, 1956],No. 9772/57. Class 110(3). In a turbine means are provided for producing along at least a portion of the surface of at least some of the rotor blades, a laminar flow of a gaseous fluid cooler than the turbine working fluid, the blades being so disposed as to produce an acceleration of the turbine working fluid sufficient to stabilize the laminar flow. Means are also provided to prevent gas leakage between the tips of the rotor blades and the turbine stator. The blade 1 shown in Fig. 1 has a pair of shields 2 disposed along its leading edge, fluid under pressure being supplied through ducts 4 to the passages between the shields and the blade proper, the fluid discharging through gaps 3 and flowing over the concave and convex surfaces of the blade so as to provide a cool insulating layer between the turbine working fluid and the blade. The shields 2 are secured by means of a pin 29 which engages extensions of the shields which are entered in a slot 31 in the blade proper. The shields are also supported by means of flanges 32 thereon which are secured to the rotor periphery. A further supply of insulating fluid from the duct 5 issues through a slot 6 formed by a further shield 7 mounted on the convex side of the blade. The trailing edge of the blade is formed by a hollow member 9 to which fluid under pressure is supplied through ducts 10. The hollow member 9 and the shield 7 are supported by pins 29 and flanges 32 similarly to the shields 2. The means to prevent leakage of working fluid past the blade tips is shown in Fig. 21 and comprises an annular chamber formed in the stator casing 11 around the rotor blade tips, a ring member 12 of graphite being supported in the annular chamber closely adjacent the rotor blade tips so that no damage will occur should the blade tips come in contact with the graphite ring. Fluid under pressure discharging from the hollow member 9 causes any working fluid which has flowed in the clearance space 14 between the blade tips and the graphite ring to flow around the passage 15 and then to rejoin the working fluid flowing into the spaces between the rotor blades. In Figs. 31 and 32 an annular channel 16 is formed in the stator casing and partitions 18 extend between the hollow portions 9 of the blades. Air under pressure issuing from the hollow portions prevents working fluid leakage across the rotor blade tips. In Fig. 6 a shroud band 34 is secured to the rotor blade tips, the shroud band having apertures 33 through which air under pressure from the hollow members 9 of the blades 1 may pass. In this embodiment atomized liquid such as water is supplied through injectors 46 into the air under pressure passing to the hollow members 9. The shroud band 34 is formed so as to provide an annular expansion chamber 421 in which are disposed vanes 472, also an annular channel 38 in which are disposed vanes 471. The chamber 421 and the channel 38 are connected by ducts 48 and the channel is divided into two by means of a flange 39 of the stator casing. The water droplets in the air are separated out in the chamber 421 and the water passes to the annular groove 38 where it forms a sealing device to prevent leakage of fluid past the blade tips. The acceleration of the working fluid in the passages between the blades which is provided so as to stabilize the laminar flow of the gaseous fluid under pressure, is caused by giving the passages a convergent shape whereby the working fluid undergoes a partial expansion so producing a reaction effect.
GB9772/57A 1956-03-28 1957-03-25 Improvements in turbines and in particular gas turbines Expired GB825967A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR711564 1956-03-28
FR718343 1956-07-10

Publications (1)

Publication Number Publication Date
GB825967A true GB825967A (en) 1959-12-23

Family

ID=26183030

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9772/57A Expired GB825967A (en) 1956-03-28 1957-03-25 Improvements in turbines and in particular gas turbines

Country Status (5)

Country Link
US (1) US3011762A (en)
CH (1) CH368973A (en)
DE (1) DE1110469B (en)
FR (1) FR1155958A (en)
GB (1) GB825967A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0140818A1 (en) * 1983-11-03 1985-05-08 United Technologies Corporation Active clearance control
EP0141770A1 (en) * 1983-11-03 1985-05-15 United Technologies Corporation Active clearance control
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
EP0497574A1 (en) * 1991-01-30 1992-08-05 United Technologies Corporation Fan case treatment

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US2916332A (en) * 1958-09-08 1959-12-08 Vladimir H Pavlecka Aerostatic bearings with fluid-dynamic seals
US3409968A (en) * 1966-10-03 1968-11-12 Borg Warner Method of making a slotted blade by extruding
US3597102A (en) * 1968-06-10 1971-08-03 English Electric Co Ltd Turbines
BE747870A (en) * 1969-03-27 1970-09-24 Aerospatiale IMPROVEMENTS TO FAIRINGS FOR PROPELLERS OR FANS
DE2231426C3 (en) * 1972-06-27 1974-11-28 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Shroudless, internally cooled axial turbine rotor blade
US3897169A (en) * 1973-04-19 1975-07-29 Gen Electric Leakage control structure
US4130373A (en) * 1976-11-15 1978-12-19 General Electric Company Erosion suppression for liquid-cooled gas turbines
JPS5477820A (en) * 1977-12-02 1979-06-21 Hitachi Ltd Method of cooling gas turbine blade
US4238170A (en) * 1978-06-26 1980-12-09 United Technologies Corporation Blade tip seal for an axial flow rotary machine
US4335885A (en) * 1980-08-19 1982-06-22 Mechanical Technology Incorporated Plural fluid magnetic/centrifugal seal
DE3308140C2 (en) * 1983-03-08 1985-12-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Multi-stage gas turbine
US4928978A (en) * 1988-04-07 1990-05-29 United Technologies Corporation Rotating shaft seal
JPH04132899A (en) * 1990-09-25 1992-05-07 Mitsubishi Heavy Ind Ltd Axial blower
US5282718A (en) * 1991-01-30 1994-02-01 United Technologies Corporation Case treatment for compressor blades
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US6430931B1 (en) * 1997-10-22 2002-08-13 General Electric Company Gas turbine in-line intercooler
US6935833B2 (en) * 2002-02-28 2005-08-30 Mtu Aero Engines Gmbh Recirculation structure for turbo chargers
US6994514B2 (en) * 2002-11-20 2006-02-07 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine
JP4821351B2 (en) * 2006-02-08 2011-11-24 トヨタ自動車株式会社 Chip turbine fan
US7887300B2 (en) * 2007-02-27 2011-02-15 Siemens Energy, Inc. CMC airfoil with thin trailing edge
DE102008037154A1 (en) * 2008-08-08 2010-02-11 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine
US7956486B2 (en) * 2009-05-23 2011-06-07 Abel Echemendia Windmill electric generator for hydroelectric power system
FR2949518B1 (en) * 2009-08-31 2011-10-21 Snecma TURBOMACHINE COMPRESSOR HAVING AIR INJECTORS
DE102013210168A1 (en) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Structural assembly for a turbomachine
WO2017176723A1 (en) * 2016-04-04 2017-10-12 Siemens Energy, Inc. Metal trailing edge for laminated cmc turbine vanes and blades
US10315754B2 (en) 2016-06-10 2019-06-11 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10106246B2 (en) 2016-06-10 2018-10-23 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10683076B2 (en) 2017-10-31 2020-06-16 Coflow Jet, LLC Fluid systems that include a co-flow jet
US11293293B2 (en) 2018-01-22 2022-04-05 Coflow Jet, LLC Turbomachines that include a casing treatment
US11111025B2 (en) 2018-06-22 2021-09-07 Coflow Jet, LLC Fluid systems that prevent the formation of ice
US11920617B2 (en) 2019-07-23 2024-03-05 Coflow Jet, LLC Fluid systems and methods that address flow separation

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0140818A1 (en) * 1983-11-03 1985-05-08 United Technologies Corporation Active clearance control
EP0141770A1 (en) * 1983-11-03 1985-05-15 United Technologies Corporation Active clearance control
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
EP0497574A1 (en) * 1991-01-30 1992-08-05 United Technologies Corporation Fan case treatment

Also Published As

Publication number Publication date
FR1155958A (en) 1958-05-12
DE1110469B (en) 1961-07-06
US3011762A (en) 1961-12-05
CH368973A (en) 1963-04-30

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