GB806207A - Improvements in or relating to governors, more particularly for gas turbine engines - Google Patents
Improvements in or relating to governors, more particularly for gas turbine enginesInfo
- Publication number
- GB806207A GB806207A GB31929/55A GB3192955A GB806207A GB 806207 A GB806207 A GB 806207A GB 31929/55 A GB31929/55 A GB 31929/55A GB 3192955 A GB3192955 A GB 3192955A GB 806207 A GB806207 A GB 806207A
- Authority
- GB
- United Kingdom
- Prior art keywords
- chamber
- valve
- fuel
- pressure
- engine
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
806,207. Gas turbines. BENDIX AVIATION CORPORATION. Nov. 8, 1955 [Dec. 22, 1954], No. 31929/55. Class 110 (3). [Also in Group XXIX] An engine speed governor, more especially for controlling the fuel supply to a gas turbine engine comprises fly weights 142 driven by the engine and acting on a valve member 176 which controls the pressure in a chamber 72 acting on a combined servo piston and fuel control valve 60. The member 60 reciprocates in a fixed sleeve 42 and has a control portion 64 coacting with ports 54 in the sleeve to control the flow of fuel from an inlet 24 to an outlet 17. Fuel under pressure also passes through a passage 110 and valve 112 to a chamber 70 where a pressure maintained at a constant value by the valve 112 acts on a piston portion 66 of the member 60 to bias the latter towards the right. Pressure fluid from the chamber 70 also passes through a passage 108 and restriction 118 to the chamber 72 where it acts on a piston portion of larger area than the portion 66. A leakage of pressure fluid from the chamber 72 through passages 120, 122 is controlled by the valve member 176 coacting with a seating 124 carried by the member 60 whereby movement of the valve member 176 is followed up by a corresponding movement of the member 60. A drain passage 100 leading from an annular groove 98 prevents the pressure in the chamber 72 from being affected by that in chamber 58. In the event of the member 60 failing to operate in response to operation of the valve member 176 an extension 178 of the latter, which has a lostmotion connection with the members 60, 124, operates the member 60 directly. A governor loading spring 162 is adjustable by an operator through a movable sleeve 160 slidable on a fixed sleeve 134. The degree of opening of the fuel valve 64 during acceleration of the engine is limited by a stop 86 which is adjustable by engine speed and compressor inlet temperature and coacts with an abutment 82 carried by the member 60. The abutment 82 also coacts with an adjustable minimum fuel flow stop 84.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US806207XA | 1954-12-22 | 1954-12-22 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB806207A true GB806207A (en) | 1958-12-23 |
Family
ID=22158525
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB31929/55A Expired GB806207A (en) | 1954-12-22 | 1955-11-08 | Improvements in or relating to governors, more particularly for gas turbine engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB806207A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3076311A (en) * | 1959-07-03 | 1963-02-05 | Rolls Royce | Gas turbine engine fuel system |
CN111852661A (en) * | 2020-05-22 | 2020-10-30 | 中国航发贵州红林航空动力控制科技有限公司 | High-pressure large-flow valve assembly |
-
1955
- 1955-11-08 GB GB31929/55A patent/GB806207A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3076311A (en) * | 1959-07-03 | 1963-02-05 | Rolls Royce | Gas turbine engine fuel system |
CN111852661A (en) * | 2020-05-22 | 2020-10-30 | 中国航发贵州红林航空动力控制科技有限公司 | High-pressure large-flow valve assembly |
CN111852661B (en) * | 2020-05-22 | 2022-08-05 | 中国航发贵州红林航空动力控制科技有限公司 | High-pressure large-flow valve assembly |
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