GB926160A - A gas turbine with preheating and cooling of the turbine rotor - Google Patents
A gas turbine with preheating and cooling of the turbine rotorInfo
- Publication number
- GB926160A GB926160A GB44099/59A GB4409959A GB926160A GB 926160 A GB926160 A GB 926160A GB 44099/59 A GB44099/59 A GB 44099/59A GB 4409959 A GB4409959 A GB 4409959A GB 926160 A GB926160 A GB 926160A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- coolant
- rotor
- nozzles
- disc
- 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
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
-
- 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
- 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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
926,160. Gas turbine engines. GENERAL ELECTRIC CO. Dec. 29, 1959 [Dec. 29, 1958], No. 44099/59. Class 110 (3). In a gas turbine having passage means in communication with the compressor discharge side and which establish a flow path around the inner portion of at least the first stage rotor disc and which form nozzle members 17, said nozzle members being rearwardly directed relative to the direction of rotation of the rotor. Coolant flows from a chamber 9c, through nozzles 9d, which are inwardly tapered and rearwardly directed relative to the direction of rotation of the rotor, thereby imparting rotational energy to the cylinder 9 to reduce the pressure and temperature of the coolant. The nozzle members 17 are machined in trapezoidal blocks, the coolant passing through a nozzle 17b via a cylindrical chamber 17a. The blocks also serve as heads of bolt members 17c, which hold the turbine discs 2a, 2b together. From the nozzles 17b part of the coolant flows along the rear face of the disc 2a, while the remainder of the coolant passes through a sealing ring member 15 to cool the front of the second turbine disc 2b. The fluid flow through the nozzles 17b also imparts rotational energy to the turbine rotor. On starting the flow of coolant will heat the turbine discs sufficiently to eliminate dangerous thermal stress gradients until normal running temperatures are reached.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US783376A US3043561A (en) | 1958-12-29 | 1958-12-29 | Turbine rotor ventilation system |
Publications (1)
Publication Number | Publication Date |
---|---|
GB926160A true GB926160A (en) | 1963-05-15 |
Family
ID=25129059
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB44099/59A Expired GB926160A (en) | 1958-12-29 | 1959-12-29 | A gas turbine with preheating and cooling of the turbine rotor |
Country Status (3)
Country | Link |
---|---|
US (1) | US3043561A (en) |
CH (1) | CH378100A (en) |
GB (1) | GB926160A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2633291A1 (en) * | 1976-07-23 | 1978-01-26 | Kraftwerk Union Ag | GAS TURBINE SYSTEM WITH COOLING THROUGH TWO SEPARATE COOLING AIR FLOWS |
EP0037897A1 (en) * | 1980-04-15 | 1981-10-21 | M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft | Means for internally cooling a gas turbine |
WO1999006671A1 (en) * | 1997-07-31 | 1999-02-11 | Siemens Aktiengesellschaft | Distribution of cooling air in a turbine stage of a gas turbine |
Families Citing this family (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3230710A (en) * | 1962-12-24 | 1966-01-25 | Garrett Corp | Gas turbine |
GB1152331A (en) * | 1966-05-18 | 1969-05-14 | Rolls Royce | Improvements in Gas Turbine Blade Cooling |
US3631672A (en) * | 1969-08-04 | 1972-01-04 | Gen Electric | Eductor cooled gas turbine casing |
US3632221A (en) * | 1970-08-03 | 1972-01-04 | Gen Electric | Gas turbine engine cooling system incorporating a vortex shaft valve |
US3748056A (en) * | 1971-02-09 | 1973-07-24 | Nissan Motor | Turbine blade cooling |
US3904307A (en) * | 1974-04-10 | 1975-09-09 | United Technologies Corp | Gas generator turbine cooling scheme |
US4008977A (en) * | 1975-09-19 | 1977-02-22 | United Technologies Corporation | Compressor bleed system |
GB2042086B (en) * | 1979-02-26 | 1983-10-12 | Gen Electric | Gas turbine engine seal |
US4332133A (en) * | 1979-11-14 | 1982-06-01 | United Technologies Corporation | Compressor bleed system for cooling and clearance control |
US4453888A (en) * | 1981-04-01 | 1984-06-12 | United Technologies Corporation | Nozzle for a coolable rotor blade |
US4543038A (en) * | 1982-03-08 | 1985-09-24 | The Garrett Corporation | Sealing apparatus and method and machinery utilizing same |
US4674955A (en) * | 1984-12-21 | 1987-06-23 | The Garrett Corporation | Radial inboard preswirl system |
US4759688A (en) * | 1986-12-16 | 1988-07-26 | Allied-Signal Inc. | Cooling flow side entry for cooled turbine blading |
FR2614654B1 (en) * | 1987-04-29 | 1992-02-21 | Snecma | TURBOMACHINE AXIAL COMPRESSOR DISC WITH CENTRIPTED AIR TAKE-OFF |
GB9723268D0 (en) * | 1997-11-05 | 1998-01-07 | Rolls Royce Plc | Turbine |
DE10159670A1 (en) * | 2001-12-05 | 2003-06-18 | Rolls Royce Deutschland | Vortex rectifier in the high pressure compressor of a gas turbine |
FR2851010B1 (en) * | 2003-02-06 | 2005-04-15 | Snecma Moteurs | DEVICE FOR VENTILATION OF A HIGH PRESSURE TURBINE ROTOR OF A TURBOMACHINE |
FR2881794B1 (en) * | 2005-02-09 | 2007-04-20 | Snecma Moteurs Sa | TURBOMACHINE WITH A NOISE REDUCTION MEANS |
GB0603030D0 (en) * | 2006-02-15 | 2006-03-29 | Rolls Royce Plc | Gas turbine engine rotor ventilation arrangement |
US8677766B2 (en) * | 2010-04-12 | 2014-03-25 | Siemens Energy, Inc. | Radial pre-swirl assembly and cooling fluid metering structure for a gas turbine engine |
RU2443882C1 (en) * | 2010-08-23 | 2012-02-27 | Открытое акционерное общество "Авиадвигатель" | Gas turbine engine |
GB201103890D0 (en) * | 2011-03-08 | 2011-04-20 | Rolls Royce Plc | Gas turbine engine swirled cooling air |
US20130051974A1 (en) * | 2011-08-25 | 2013-02-28 | Honeywell International Inc. | Gas turbine engines and methods for cooling components thereof with mid-impeller bleed cooling air |
CN103046964B (en) * | 2012-06-27 | 2015-12-09 | 北京航空航天大学 | A kind of aero-engine turbine disk based on active temperature gradient proof stress |
JP6432110B2 (en) * | 2014-08-29 | 2018-12-05 | 三菱日立パワーシステムズ株式会社 | gas turbine |
FR3048998B1 (en) * | 2016-03-16 | 2019-12-13 | Safran Aircraft Engines | TURBINE ROTOR COMPRISING A VENTILATION SPACER |
CN106640212B (en) * | 2016-11-04 | 2019-07-02 | 北京航空航天大学 | A kind of oblique nozzle of air supply of prewhirling of aero gas turbine engine high-pressure turbine disk chamber cooling air |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2369795A (en) * | 1941-11-17 | 1945-02-20 | Andre P E Planiol | Gaseous fluid turbine or the like |
US2632626A (en) * | 1947-02-12 | 1953-03-24 | United Aircraft Corp | Dirt trap for turbine cooling air |
US2639579A (en) * | 1949-06-21 | 1953-05-26 | Hartford Nat Bank & Trust Co | Turbojet engine having tail pipe ejector to induce flow of cooling air |
US2680001A (en) * | 1950-11-13 | 1954-06-01 | United Aircraft Corp | Arrangement for cooling turbine bearings |
US2858101A (en) * | 1954-01-28 | 1958-10-28 | Gen Electric | Cooling of turbine wheels |
-
1958
- 1958-12-29 US US783376A patent/US3043561A/en not_active Expired - Lifetime
-
1959
- 1959-12-22 CH CH8225859A patent/CH378100A/en unknown
- 1959-12-29 GB GB44099/59A patent/GB926160A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2633291A1 (en) * | 1976-07-23 | 1978-01-26 | Kraftwerk Union Ag | GAS TURBINE SYSTEM WITH COOLING THROUGH TWO SEPARATE COOLING AIR FLOWS |
EP0037897A1 (en) * | 1980-04-15 | 1981-10-21 | M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft | Means for internally cooling a gas turbine |
WO1999006671A1 (en) * | 1997-07-31 | 1999-02-11 | Siemens Aktiengesellschaft | Distribution of cooling air in a turbine stage of a gas turbine |
US6231303B1 (en) | 1997-07-31 | 2001-05-15 | Siemens Aktiengesellschaft | Gas turbine having a turbine stage with cooling-air distribution |
Also Published As
Publication number | Publication date |
---|---|
CH378100A (en) | 1964-05-31 |
US3043561A (en) | 1962-07-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB926160A (en) | A gas turbine with preheating and cooling of the turbine rotor | |
US2584899A (en) | Construction of stator elements of turbines, compressors, or like machines | |
US3565545A (en) | Cooling of turbine rotors in gas turbine engines | |
US5755556A (en) | Turbomachine rotor with improved cooling | |
US4466239A (en) | Gas turbine engine with improved air cooling circuit | |
US5685158A (en) | Compressor rotor cooling system for a gas turbine | |
US3742706A (en) | Dual flow cooled turbine arrangement for gas turbine engines | |
US3286461A (en) | Turbine starter and cooling | |
US4320903A (en) | Labyrinth seals | |
JP4746325B2 (en) | Gas turbine engine component having a bypass circuit | |
US4456427A (en) | Cooling air injector for turbine blades | |
US6382903B1 (en) | Rotor bore and turbine rotor wheel/spacer heat exchange flow circuit | |
GB1330893A (en) | Gas turbine engine shroud assemblies | |
GB645848A (en) | Improvements in or relating to elastic fluid actuated power systems | |
US3453825A (en) | Gas turbine engine having turbine discs with reduced temperature differential | |
JP2015514928A (en) | Air accelerator on tie rod in turbine disc bore | |
US3907457A (en) | Labyrinth structure for air outlet of gas turbine engine bearing chamber | |
RU94026895A (en) | Single-shaft stationary gas turbine | |
GB730506A (en) | Improvements in or relating to gas turbine engines | |
US3756019A (en) | Gas turbine blade arrangement | |
CA2245639A1 (en) | Recovery type steam-cooled gas turbine | |
GB938247A (en) | Gas turbine engine having cooled turbine blading | |
US2891382A (en) | Liquid-cooled turbine | |
US4358926A (en) | Turbine engine with shroud cooling means | |
GB1158634A (en) | Improvements in Gas Turbine Engines |