GB831982A - Starting control for gas turbine engines - Google Patents
Starting control for gas turbine enginesInfo
- Publication number
- GB831982A GB831982A GB30171/56A GB3017156A GB831982A GB 831982 A GB831982 A GB 831982A GB 30171/56 A GB30171/56 A GB 30171/56A GB 3017156 A GB3017156 A GB 3017156A GB 831982 A GB831982 A GB 831982A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuel
- valve
- actuated
- manifold pressure
- main
- 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
- F02C7/26—Starting; Ignition
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluid-Driven Valves (AREA)
Abstract
831,982. Gas-turbine plant. BENDIXAVIATION CORPORATION. Oct. 3, 1956[Oct. 24, 1995], No. 30171/56. Class 110 (3).[Also in Group XXIX] A fuel control system for gas-turbine engines has a fuel manifold 18, a main fuel flow path 11, 13 supplying fuel from a source to the engine and containing a main control means 12 regulating flow, a second fuel flow path 38, 40 connected to the source, a second control means, e.g. valve 36, actuated, e.g. by a diaphragm 46 in response to manifold pressure to deliver fuel through the second path in addition to that delivered by the main path until a predetermined manifold pressure is reached. This predetermined pressure acts via a restriction 48 to lower piston valve 36 and close the by-pass around the valve 12. In a second embodiment the valve 36 is actuated by a differential piston, the small end being exposed to manifold pressure via a restriction and the large end similarly exposed through an orifice adjustable by a thermally actuated needle valve responsive to fuel temperature.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US831982XA | 1955-10-24 | 1955-10-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB831982A true GB831982A (en) | 1960-04-06 |
Family
ID=22176799
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB30171/56A Expired GB831982A (en) | 1955-10-24 | 1956-10-03 | Starting control for gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB831982A (en) |
-
1956
- 1956-10-03 GB GB30171/56A patent/GB831982A/en not_active Expired
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