GB837309A - Improvements in or relating to gas-turbine engines - Google Patents
Improvements in or relating to gas-turbine enginesInfo
- Publication number
- GB837309A GB837309A GB34217/56A GB3421756A GB837309A GB 837309 A GB837309 A GB 837309A GB 34217/56 A GB34217/56 A GB 34217/56A GB 3421756 A GB3421756 A GB 3421756A GB 837309 A GB837309 A GB 837309A
- Authority
- GB
- United Kingdom
- Prior art keywords
- tube
- pressure
- chamber
- turbine
- pump
- 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
- 239000000446 fuel Substances 0.000 abstract 4
- 239000003921 oil Substances 0.000 abstract 3
- 238000002485 combustion reaction Methods 0.000 abstract 2
- 239000010687 lubricating oil Substances 0.000 abstract 2
- 239000002775 capsule Substances 0.000 abstract 1
- 150000001875 compounds Chemical class 0.000 abstract 1
- 239000012530 fluid Substances 0.000 abstract 1
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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/06—Shutting-down
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Control Of Turbines (AREA)
Abstract
837,309. Gas-turbine plant. ROLLSROYCE Ltd. Oct. 28, 1957 [Nov. 8, 1956], No. 34217/66. Class 110 (3). [Also in Groups XXIV and XXIX] A gas-turbine engine comprising a turbine and a coaxial driven member interconnected by a driving shaft has a tube or the equivalent located within and connected at spaced locations to the shaft, one location being in the region of the load and another location being in the region of the turbine rotor, the tube or equivalent being fed with a fluid under pressure so as to provide a pressurized chamber which is connected to pressure responsive means controlling the fuel supply, the arrangement being such that when the driving shaft fractures, the tube or equivalent also fractures resulting in reduction of pressure on the pressure-responsive means and so reducing the engine fuel supply. An axial flow compressor 10a, 10b supplies combustion air to combustion equipment 11 feeding a turbine 13b driving the compressor through a hollow driving shaft 14. Fuel is supplied to the injector nozzles 12 by a swashplate pump 15 the delivery of which is controlled by a unit 16. The angle of the swashplate is controlled by a piston 21 the position of which determined by the amount of leak-off from the chamber 23. The control unit 16 comprises a flexible diaphragm 29 carrying a lever 30 loaded by an evacuated capsule 35 responsive to changes in atmospheric pressure, and a piston 33 acted upon by the pump delivery pressure and a spring 31. The lever 30 carries a valve element 28 which opens or closes the end of the vent pipe 27 so that an increase of atmospheric pressure or a decrease of pump delivery pressure will cause an increase in the fuel delivery from the pump and vice versa. A lubricating oil pump 37 delivers oil through a pipe 38 and muff 39 to a tube 40 supplying oil to the engine bearings. The tube 40 is connected to the rotor system by splines 41, 42. A constriction 45 in the tube 40 forms a chamber 46 having a restricted oil inlet. The wall of the chamber 46 is provided with a shear neck in the form of a helical groove 47. The chamber 46 is connected by ducting 48 to a chamber 53 having one wall formed by a flexible diaphragm 51. The diaphragm 51 carries a leak-off valve 59 which is urged to the open position by a spring 56 and to the closed position by the pressure in the chamber 53. In the event of failure of the driving shaft 14, the tube 40 will be quickly fractured in the region of the shear neck 47. The pressure in the chambers 46 and 53 falls and the spring 56 opens the valve 59 which causes the delivery of the pump 15 to be reduced rapidly. A deaerator 49 separates air from the lubricating oil. A flanged plug 65 which is rotatable relative to the tube 40 and the turbine casing forms a connection between the ducting 48 and tube 40. The invention can be applied to a gas-turbine plant driving a propeller or to a compound gas-turbine engine.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB34217/56A GB837309A (en) | 1956-11-08 | 1956-11-08 | Improvements in or relating to gas-turbine engines |
DE1957R0022091 DE1072014B (en) | 1956-11-08 | 1957-10-30 | |
US693297A US2930188A (en) | 1956-11-08 | 1957-10-30 | Gas-turbine engine with failure-operated control means |
FR1185633D FR1185633A (en) | 1956-11-08 | 1957-10-31 | Development of gas turbine engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB34217/56A GB837309A (en) | 1956-11-08 | 1956-11-08 | Improvements in or relating to gas-turbine engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB837309A true GB837309A (en) | 1960-06-09 |
Family
ID=10362852
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB34217/56A Expired GB837309A (en) | 1956-11-08 | 1956-11-08 | Improvements in or relating to gas-turbine engines |
Country Status (4)
Country | Link |
---|---|
US (1) | US2930188A (en) |
DE (1) | DE1072014B (en) |
FR (1) | FR1185633A (en) |
GB (1) | GB837309A (en) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3159166A (en) * | 1961-10-16 | 1964-12-01 | Gen Motors Corp | Engine safety control |
US3498282A (en) * | 1967-12-21 | 1970-03-03 | Donald P Dattilo | Mechanism for automatically stopping internal combustion engines |
FR2317501A1 (en) * | 1975-07-09 | 1977-02-04 | Snecma | COUPLING DEVICE FOR GAS TURBINE ENGINE |
US4389984A (en) * | 1981-03-26 | 1983-06-28 | Destrampe Terry G | Post-shutdown coolant-supply device |
GB2124788B (en) * | 1982-06-30 | 1986-05-21 | Rolls Royce | Torque-sensitive control of gas turbines |
DE4341445A1 (en) * | 1993-12-06 | 1995-06-08 | Bmw Rolls Royce Gmbh | Mechanical shut-off system for gas turbine fuel supply |
US6607349B2 (en) * | 2001-11-14 | 2003-08-19 | Honeywell International, Inc. | Gas turbine engine broken shaft detection system |
US7654093B2 (en) * | 2005-09-26 | 2010-02-02 | Pratt & Whitney Canada Corp. | Method of adjusting a triggering clearance and a trigger |
US8567564B2 (en) * | 2008-03-20 | 2013-10-29 | United Technologies Corporation | Non-interrupted oil supply for gas turbine engine |
US9291070B2 (en) | 2010-12-03 | 2016-03-22 | Pratt & Whitney Canada Corp. | Gas turbine rotor containment |
US10316689B2 (en) | 2016-08-22 | 2019-06-11 | Rolls-Royce Corporation | Gas turbine engine health monitoring system with shaft-twist sensors |
EP3382160B1 (en) * | 2017-03-28 | 2020-10-21 | Ge Avio S.r.l. | Gas turbine engine turning system and operating method thereof |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2551429A (en) * | 1948-11-19 | 1951-05-01 | Ingersoll Rand Co | Safety trip device for motors responsive to temperature, speed, and pressure |
US2693248A (en) * | 1950-05-03 | 1954-11-02 | Gen Motors Corp | Lubrication system |
US2676458A (en) * | 1951-09-17 | 1954-04-27 | Boeing Co | Gas turbine combined lubricating, and fuel supply system having centrifugal means topurify and circulate fuel |
-
1956
- 1956-11-08 GB GB34217/56A patent/GB837309A/en not_active Expired
-
1957
- 1957-10-30 US US693297A patent/US2930188A/en not_active Expired - Lifetime
- 1957-10-30 DE DE1957R0022091 patent/DE1072014B/de active Pending
- 1957-10-31 FR FR1185633D patent/FR1185633A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
US2930188A (en) | 1960-03-29 |
FR1185633A (en) | 1959-08-03 |
DE1072014B (en) | 1959-12-24 |
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