GB988541A - Gas turbine rotor cooling - Google Patents
Gas turbine rotor coolingInfo
- Publication number
- GB988541A GB988541A GB851862A GB851862A GB988541A GB 988541 A GB988541 A GB 988541A GB 851862 A GB851862 A GB 851862A GB 851862 A GB851862 A GB 851862A GB 988541 A GB988541 A GB 988541A
- Authority
- GB
- United Kingdom
- Prior art keywords
- discs
- passages
- interstage
- gas turbine
- blade
- 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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
988,541. Gas turbine rotor cooling. RUSHTON & HORNSBY Ltd. Jan. 4, 1963 [March 6, 1962], No. 8518/62. Headings F1G and F1T. The rotor and blade roots of an axial flow gas turbine having blade carrying discs spaced axially apart by rotating sealing rings secured therebetween are cooled by fluid passing through passages between the discs and sealing rings to an area in the region of the blade roots enclosed by annular plates on either side of each disc, the plate on the interstage side of each disc being located at its radially outer edge by the blade platforms and at its radially inner edge by an extension on the interstage sealing ring. An axial flow gas turbine has rotor discs 11, 12 carrying blades 13, 14 separated by a sealing ring 15 attached to the discs. The upstream and downstream rims of discs 11, 12 are enclosed by annular plates 25, 26 respectively, retained between blade platforms 19, 20 and slots in the disc rims. The interstage rims of discs 11, 12 are enclosed by annular plates 27, 28 secured to blade platforms 19, 20 by circlips 29, 30 and engaging extensions 32, 33 on sealing ring 15. Plates 27, 28 may be tapered radially outwards and may be locked to ring 15 by dowels. Cooling fluid flows respectively through passages 34, 36 to space 38 from which it exhausts through holes 37, 39 and through passages 35, 40 to exhaust through holes 41, 42. The blades 13, 14 may also have internal cooling passages. In a modification, Fig. 2 (not shown), the sealing ring has additional cooling passages and the interstage annular plates are split and not retained by circlips.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB851862A GB988541A (en) | 1962-03-06 | 1962-03-06 | Gas turbine rotor cooling |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB851862A GB988541A (en) | 1962-03-06 | 1962-03-06 | Gas turbine rotor cooling |
Publications (1)
Publication Number | Publication Date |
---|---|
GB988541A true GB988541A (en) | 1965-04-07 |
Family
ID=9853976
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB851862A Expired GB988541A (en) | 1962-03-06 | 1962-03-06 | Gas turbine rotor cooling |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB988541A (en) |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2503246A1 (en) * | 1981-04-01 | 1982-10-08 | United Technologies Corp | NOZZLE FOR COOLING ROTOR BLADE |
US4551063A (en) * | 1983-03-18 | 1985-11-05 | Kraftwerke Union Ag | Medium-pressure steam turbine |
US4582467A (en) * | 1983-12-22 | 1986-04-15 | United Technologies Corporation | Two stage rotor assembly with improved coolant flow |
US4645424A (en) * | 1984-07-23 | 1987-02-24 | United Technologies Corporation | Rotating seal for gas turbine engine |
US4659289A (en) * | 1984-07-23 | 1987-04-21 | United Technologies Corporation | Turbine side plate assembly |
US4730983A (en) * | 1986-09-03 | 1988-03-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | System for attaching a rotor blade to a rotor disk |
US4730982A (en) * | 1986-06-18 | 1988-03-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Assembly for controlling the flow of cooling air in an engine turbine |
US4880354A (en) * | 1987-11-25 | 1989-11-14 | Hitachi, Ltd. | Warming structure of gas turbine rotor |
US5941687A (en) * | 1996-11-12 | 1999-08-24 | Rolls-Royce Plc | Gas turbine engine turbine system |
US6382903B1 (en) | 1999-03-03 | 2002-05-07 | General Electric Company | Rotor bore and turbine rotor wheel/spacer heat exchange flow circuit |
GB2413598A (en) * | 2004-05-01 | 2005-11-02 | Rolls Royce Plc | Providing cooling gas to turbine blade and disc in gas turbine engine |
GB2427657A (en) * | 2005-06-28 | 2007-01-03 | Siemens Ind Turbomachinery Ltd | Cooling arrangement in a device/machine such as a gas turbine engine |
WO2012076588A1 (en) * | 2010-12-09 | 2012-06-14 | Alstom Technology Ltd | Fluid flow machine especially gas turbine penetrated axially by a hot gas stream |
EP2213836A3 (en) * | 2009-01-30 | 2014-02-19 | General Electric Company | Rotor chamber cover member having aperture for dirt separation and related turbine |
EP2924237A1 (en) * | 2014-03-25 | 2015-09-30 | Industria de Turbo Propulsores S.A. | Gas turbine rotor |
EP3495611A1 (en) * | 2017-12-06 | 2019-06-12 | Ansaldo Energia Switzerland AG | Apparatus for controlled delivery of cooling air to turbine blades in a gas turbine |
-
1962
- 1962-03-06 GB GB851862A patent/GB988541A/en not_active Expired
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2503246A1 (en) * | 1981-04-01 | 1982-10-08 | United Technologies Corp | NOZZLE FOR COOLING ROTOR BLADE |
US4551063A (en) * | 1983-03-18 | 1985-11-05 | Kraftwerke Union Ag | Medium-pressure steam turbine |
US4582467A (en) * | 1983-12-22 | 1986-04-15 | United Technologies Corporation | Two stage rotor assembly with improved coolant flow |
US4645424A (en) * | 1984-07-23 | 1987-02-24 | United Technologies Corporation | Rotating seal for gas turbine engine |
US4659289A (en) * | 1984-07-23 | 1987-04-21 | United Technologies Corporation | Turbine side plate assembly |
US4730982A (en) * | 1986-06-18 | 1988-03-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Assembly for controlling the flow of cooling air in an engine turbine |
US4730983A (en) * | 1986-09-03 | 1988-03-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | System for attaching a rotor blade to a rotor disk |
US4880354A (en) * | 1987-11-25 | 1989-11-14 | Hitachi, Ltd. | Warming structure of gas turbine rotor |
US5941687A (en) * | 1996-11-12 | 1999-08-24 | Rolls-Royce Plc | Gas turbine engine turbine system |
US6382903B1 (en) | 1999-03-03 | 2002-05-07 | General Electric Company | Rotor bore and turbine rotor wheel/spacer heat exchange flow circuit |
GB2413598A (en) * | 2004-05-01 | 2005-11-02 | Rolls Royce Plc | Providing cooling gas to turbine blade and disc in gas turbine engine |
GB2427657A (en) * | 2005-06-28 | 2007-01-03 | Siemens Ind Turbomachinery Ltd | Cooling arrangement in a device/machine such as a gas turbine engine |
GB2427657B (en) * | 2005-06-28 | 2011-01-19 | Siemens Ind Turbomachinery Ltd | A gas turbine engine |
EP2213836A3 (en) * | 2009-01-30 | 2014-02-19 | General Electric Company | Rotor chamber cover member having aperture for dirt separation and related turbine |
WO2012076588A1 (en) * | 2010-12-09 | 2012-06-14 | Alstom Technology Ltd | Fluid flow machine especially gas turbine penetrated axially by a hot gas stream |
RU2548226C2 (en) * | 2010-12-09 | 2015-04-20 | Альстом Текнолоджи Лтд | Fluid medium flow unit, in particular, turbine with axially passing heated gas flow |
US9657641B2 (en) | 2010-12-09 | 2017-05-23 | General Electric Company | Fluid flow machine especially gas turbine penetrated axially by a hot gas stream |
EP2924237A1 (en) * | 2014-03-25 | 2015-09-30 | Industria de Turbo Propulsores S.A. | Gas turbine rotor |
EP3495611A1 (en) * | 2017-12-06 | 2019-06-12 | Ansaldo Energia Switzerland AG | Apparatus for controlled delivery of cooling air to turbine blades in a gas turbine |
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