GB1438767A - Actuator device for use in a gas turbine engine - Google Patents
Actuator device for use in a gas turbine engineInfo
- Publication number
- GB1438767A GB1438767A GB4545572A GB4545572A GB1438767A GB 1438767 A GB1438767 A GB 1438767A GB 4545572 A GB4545572 A GB 4545572A GB 4545572 A GB4545572 A GB 4545572A GB 1438767 A GB1438767 A GB 1438767A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft
- pawl
- arm
- output shaft
- wheel
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Driving Devices And Active Controlling Of Vehicle (AREA)
- Transmission Devices (AREA)
- Hydraulic Clutches, Magnetic Clutches, Fluid Clutches, And Fluid Joints (AREA)
Abstract
1438767 Clutch control LUCAS INDUSTRIES Ltd 30 Oct 1973 [3 Oct 1972] 45455/72 Heading F2L [Also in Division F1] An actuator device for use in the control of a gas turbine engine fuel supply in an aircraft comprises an output shaft 13 coaxial with an input worm-wheel 14 (driven by a motor through a worm 16) and a manual input shaft 15, the output shaft 13 having a plate 18 fixed to it which pivotally mounts a pawl member 19 spring biased to cause the pawl 19 to engage the teeth of the worm-wheel 14 and connect together input wheel 14 and output shaft 13, and the input shaft 15 having an arm 20 which mounts a pawl member 21 which can engage a notch 18b (not shown) in the plate 18 to connect shaft 15 and output shaft 13 together and simultaneously pivot pawl member 19 through engagement with an extension 19a to disengage wheel 14 from the output member 13. The pawl member 21 supports a roller 22 which runs on a cam track 23 fixed to the body of the actuator, the cam track defining a region in which engagement of pawl 21 and notch 18b is possible (an automatic control region) and a region in which it is possible (manual control). Disengagement of shafts 15 and 13 and re-engagement of wheel 14 and shaft 13 can be accomplished either by movement back of shaft 15, which in the application to an aircraft engine causes the engine to idle as a lever 31 interlinked to a lever 30 which rotates shaft 15 is moved back, or by movement in the opposite sense (past the full speed position) which causes the arm 20 of shaft 15 to strike an abutment 24 which pivots the cam 23 to disengage pawl 21 and allow pawl 19 to re-engage. A pawl 25 linked to cam 23 as shown pivots the cam 23 back on being struck by arm 20 as the shaft 15 (i.e. lever 31) is moved back from its full speed position. The disengagement of manual control 31 from the output shaft 13 can thus occur at either full speed or idle. As shown in Fig. 2 the rotation of worm 16 is controlled by a computer 33 receiving inputs from the engine 34, a transducer 29 responsive to the position of an arm 27 connected to shaft 13 and the position of control lever 31, the output shaft 13 controlling a fuel valve 35 through arm 27.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB4545572A GB1438767A (en) | 1972-10-03 | 1972-10-03 | Actuator device for use in a gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB4545572A GB1438767A (en) | 1972-10-03 | 1972-10-03 | Actuator device for use in a gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1438767A true GB1438767A (en) | 1976-06-09 |
Family
ID=10437267
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB4545572A Expired GB1438767A (en) | 1972-10-03 | 1972-10-03 | Actuator device for use in a gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1438767A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2882097A1 (en) * | 2005-02-17 | 2006-08-18 | Hispano Suiza Sa | CONTROLLING VARIABLE GEOMETRIES OF A GAS TURBINE AIRCRAFT ENGINE |
-
1972
- 1972-10-03 GB GB4545572A patent/GB1438767A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2882097A1 (en) * | 2005-02-17 | 2006-08-18 | Hispano Suiza Sa | CONTROLLING VARIABLE GEOMETRIES OF A GAS TURBINE AIRCRAFT ENGINE |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PCNP | Patent ceased through non-payment of renewal fee |