GB655304A - Improvements in or relating to turbine cooling systems - Google Patents

Improvements in or relating to turbine cooling systems

Info

Publication number
GB655304A
GB655304A GB2766647A GB2766647A GB655304A GB 655304 A GB655304 A GB 655304A GB 2766647 A GB2766647 A GB 2766647A GB 2766647 A GB2766647 A GB 2766647A GB 655304 A GB655304 A GB 655304A
Authority
GB
United Kingdom
Prior art keywords
turbine
compressor
diffuser
working fluid
channel
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
GB2766647A
Inventor
Austingeoffrey Smith
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
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
Priority to BE485338D priority Critical patent/BE485338A/xx
Priority to NL72348D priority patent/NL72348C/xx
Priority to CH272066D priority patent/CH272066A/en
Priority to FR973487D priority patent/FR973487A/en
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB2766647A priority patent/GB655304A/en
Publication of GB655304A publication Critical patent/GB655304A/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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
    • 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
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/088—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in a closed cavity
    • 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

Abstract

655,304. Gas turbine plant. POWER JETS (Research & Development), Ltd. Oct. 15, 1948, No. 27666/47. [Class 110(iii)] In a gas turbine plant comprising a compressor which supplies working fluid successively through a diffuser, heating means and a turbine, cooling fluid is drawn from a high pressure region of the compressor system passed through the turbine structure to cool it and returned to a lower pressure region of the diffuser upstream of the heating means but downstream of the compressor. In the plant shown, Fig. 1, a multistage axial flow compressor 1 is driven by a multistage axial flow turbine 2 which is supplied with gas by a combustion chamber 7. An annular cooling channel 13 is formed around the rotor 10 by means of shroud rings 15 around the base portions 16 of blades 14. The base portions 16 are provided with radial slits to allow passage of cooling air along the channel 13. Air from the diffuser 6 is led by a pipe 18 to the hollow shaft 3 from which it passes through the impeller vanes 22 to the channel 13. The air leaving the channel 13 passes through turbine vanes 24 to the pipe 27 which returns it into the stream of working fluid at the diffuser 6 preferable downstream of an exhaust heat exchanger if such is provided. The point at which the air is returned to the working fluid has a lower pressure than the point at which it is taken. To facilitate the conduction of heat to the root of the blade, each blade may have one or more closed internal cavities containing a suitable cooling medium such as sodium, caesium, aluminium chloride or bromide. The rotor 10 of the turbine 2 is constructed of a number of discs 11 held together by a member 12 enclosed in the hollow shaft 3. In the arrangement shown in Fig. 4, each rotor element 11 has a central bore in which is fitted a header chamber 32 having radially extending hollow ribs 33, the header being connected by radial tubes 34 with ducts 35 in the blades to form a closed circuit which is filled with a cooling medium such as one of the metals or salts referred to above. The annular ports 36 and 37 are fitted with axial flow compressor and turbine blading. The invention may be applied to plant in which the working fluid is heated indirectly in a heat exchanger. Specifications 610,737, 616,672 and 623,841 are referred to.
GB2766647A 1948-10-15 1948-10-15 Improvements in or relating to turbine cooling systems Expired GB655304A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
BE485338D BE485338A (en) 1948-10-15
NL72348D NL72348C (en) 1948-10-15
CH272066D CH272066A (en) 1948-10-15 1948-10-06 Gas turbine plant.
FR973487D FR973487A (en) 1948-10-15 1948-10-14 Improvements made to turbine cooling devices
GB2766647A GB655304A (en) 1948-10-15 1948-10-15 Improvements in or relating to turbine cooling systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2766647A GB655304A (en) 1948-10-15 1948-10-15 Improvements in or relating to turbine cooling systems

Publications (1)

Publication Number Publication Date
GB655304A true GB655304A (en) 1951-07-18

Family

ID=10263287

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2766647A Expired GB655304A (en) 1948-10-15 1948-10-15 Improvements in or relating to turbine cooling systems

Country Status (5)

Country Link
BE (1) BE485338A (en)
CH (1) CH272066A (en)
FR (1) FR973487A (en)
GB (1) GB655304A (en)
NL (1) NL72348C (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1024754B (en) * 1956-02-11 1958-02-20 Maschf Augsburg Nuernberg Ag Cooled blade for hot operated turbines or compressors
DE1027013B (en) * 1954-11-29 1958-03-27 Franz Olden Gas turbine with cooling air intake on the open front face of a multi-edged hollow drum bank
GB2118630A (en) * 1982-04-19 1983-11-02 United Technologies Corp Structure for directing cooling air onto a turbine disc
WO1997049902A1 (en) * 1996-06-24 1997-12-31 Westinghouse Electric Corporation On-board auxiliary compressor for combustion turbine cooling air supply
WO1998013584A1 (en) * 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Method of compensating pressure loss in a cooling air guide system in a gas turbine plant
CN103470318A (en) * 2012-06-06 2013-12-25 通用电气公司 Method for controlling temperature of a turbine engine compressor and compressor of a turbine engine
US20160076381A1 (en) * 2014-09-17 2016-03-17 United Technologies Corporation Secondary flowpath system for a gas turbine engine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1009436B (en) * 1953-03-27 1957-05-29 Daimler Benz Ag Cooling and de-icing device for gas turbines
BE535079A (en) * 1954-01-25
GB789197A (en) * 1956-01-06 1958-01-15 British Thomson Houston Co Ltd Improvements in cooling systems for high temperature turbines
DE1115885B (en) * 1959-03-23 1961-10-26 Gen Electric Coolant shovel in a hollow compressor rotor
DE1288851B (en) * 1965-09-04 1969-02-06 Gen Electric Cooling system for thermosiphon-cooled compressor or turbine blades of a gas turbine
FR2769341B1 (en) * 1997-10-02 1999-11-19 Snecma FLUID COOLED TURBINE MONOBLOCK BLADE DISC

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1027013B (en) * 1954-11-29 1958-03-27 Franz Olden Gas turbine with cooling air intake on the open front face of a multi-edged hollow drum bank
DE1024754B (en) * 1956-02-11 1958-02-20 Maschf Augsburg Nuernberg Ag Cooled blade for hot operated turbines or compressors
GB2118630A (en) * 1982-04-19 1983-11-02 United Technologies Corp Structure for directing cooling air onto a turbine disc
WO1997049902A1 (en) * 1996-06-24 1997-12-31 Westinghouse Electric Corporation On-board auxiliary compressor for combustion turbine cooling air supply
WO1998013584A1 (en) * 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Method of compensating pressure loss in a cooling air guide system in a gas turbine plant
CN103470318A (en) * 2012-06-06 2013-12-25 通用电气公司 Method for controlling temperature of a turbine engine compressor and compressor of a turbine engine
US9267513B2 (en) 2012-06-06 2016-02-23 General Electric Company Method for controlling temperature of a turbine engine compressor and compressor of a turbine engine
CN103470318B (en) * 2012-06-06 2016-08-10 通用电气公司 Control method and the compressor of turbogenerator of turbine engine compressor temperature
US20160076381A1 (en) * 2014-09-17 2016-03-17 United Technologies Corporation Secondary flowpath system for a gas turbine engine
US10837288B2 (en) * 2014-09-17 2020-11-17 Raytheon Technologies Corporation Secondary flowpath system for a gas turbine engine

Also Published As

Publication number Publication date
NL72348C (en)
BE485338A (en)
FR973487A (en) 1951-02-12
CH272066A (en) 1950-11-30

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