GB1295092A - - Google Patents
Info
- Publication number
- GB1295092A GB1295092A GB1295092DA GB1295092A GB 1295092 A GB1295092 A GB 1295092A GB 1295092D A GB1295092D A GB 1295092DA GB 1295092 A GB1295092 A GB 1295092A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- valve
- piston
- conduit
- under pressure
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/02—De-icing means for engines having icing phenomena
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Temperature-Responsive Valves (AREA)
- Supercharger (AREA)
Abstract
1295092 Gas turbine engines; air intakes ROTAX Ltd 5 Feb 1970 [19 Feb 1969] 8892/69 Heading F1G The invention relates to a hot air system for supplying heated air to an air jacket disposed around the air intake duct of a gas turbine engine, there being conduit means through which hot air can flow to the jacket from a source thereof such as a tapping from the compressor of the engine, a control valve being disposed in the conduit, the valve being controlled by temperature sensitive means responsive to temperature of intake of air flowing in the duct. In Fig. 3 air is tapped from the engine compressor 101 and supplied through conduit 100 to the air jacket 102 around the engine air intake duct. Two control valves 111, 112 are disposed in the conduit 100, the valves being similar in construction. The valve 111 is shown in Fig.4 and comprises a casing 113 forming part of the conduit 100, a piston member comprising a skirt portion 115 and a head 116 being slidably mounted therein. The piston is also slidably mounted in a fixed housing 119a which defines with the piston head a chamber 120 to which air under pressure may be supplied to control the piston. The piston is formed with an aperture 118 also with a stop 117 which in the closed position of the valve shown abuts the end of the housing 119a, the air under pressure acting against the stop 117 holding the piston in this position. Upon actuation of solenoid 124, the two-way valve 123 opens to allow air under pressure to pass through passage 121 to chamber 120 thus causing the piston to move to the open position in which heated air passes to the jacket space 102. The opening of the valve 112 is controlled in dependence on temperature of intake air flowing through the intake duct as sensed by the device 127. The device 127 is shown in Fig.1 and comprises a mounting 10, a tubular member 12 of material having a high coefficient of thermal expansion and a tubular member 16 of material having a low coefficient of thermal expansion, the member 16 acting at its lower end through a lever assembly 29, 30 against a plug member 31 slidable in casing 27 the plug member in turn acting through a spring-loaded tube member 37 to control the opening of a valve member 32. The inlet 35 of the valve is supplied with air through restrictor 125; a tapping from a point intermediate the restrictor 125 and the temperature sensing device communicates with the chamber 120 of the valve 112. Fluid under pressure is caused to flow through member 16 and discharges through nozzle 24 to induce ambient air-flow through inlet 25 between the tubular members 12, 16.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB889269 | 1969-02-19 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1295092A true GB1295092A (en) | 1972-11-01 |
Family
ID=9861310
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1295092D Expired GB1295092A (en) | 1969-02-19 | 1969-02-19 |
Country Status (3)
Country | Link |
---|---|
DE (1) | DE2007256A1 (en) |
FR (1) | FR2035639A5 (en) |
GB (1) | GB1295092A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3009278A1 (en) * | 2013-07-30 | 2015-02-06 | Airbus Operations Sas | METHOD FOR REGULATING THE DEFROSTING OF AN AIRCRAFT ATTACHMENT EDGE AND DEVICE FOR IMPLEMENTING THE SAME |
US9341280B2 (en) | 2012-12-05 | 2016-05-17 | Airbus Operations S.A.S. | Dual regulation level valve and de-icing device for an air inlet of an aircraft engine nacelle incorporating said valve |
EP3045699A1 (en) * | 2015-01-14 | 2016-07-20 | Goodrich Actuation Systems Limited | Anti-icing systems |
EP3266712A1 (en) * | 2016-07-06 | 2018-01-10 | United Technologies Corporation | Nacelle anti ice system |
EP3259508A4 (en) * | 2015-02-16 | 2018-10-03 | Dukes Aerospace Inc. | Redundant valve system |
EP4350128A1 (en) * | 2022-10-03 | 2024-04-10 | Microtecnica S.r.l. | Pressure regulating shut-off valve |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3246781B1 (en) * | 2016-05-18 | 2020-06-24 | Microtecnica S.r.l. | Pressure regulation valve |
-
1969
- 1969-02-19 GB GB1295092D patent/GB1295092A/en not_active Expired
-
1970
- 1970-02-18 DE DE19702007256 patent/DE2007256A1/en active Pending
- 1970-02-19 FR FR7005911A patent/FR2035639A5/fr not_active Expired
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9341280B2 (en) | 2012-12-05 | 2016-05-17 | Airbus Operations S.A.S. | Dual regulation level valve and de-icing device for an air inlet of an aircraft engine nacelle incorporating said valve |
FR3009278A1 (en) * | 2013-07-30 | 2015-02-06 | Airbus Operations Sas | METHOD FOR REGULATING THE DEFROSTING OF AN AIRCRAFT ATTACHMENT EDGE AND DEVICE FOR IMPLEMENTING THE SAME |
US9346549B2 (en) | 2013-07-30 | 2016-05-24 | Airbus Operations S.A.S. | Method for regulating the de-icing of a leading edge of an aircraft and device for its implementation |
EP3045699A1 (en) * | 2015-01-14 | 2016-07-20 | Goodrich Actuation Systems Limited | Anti-icing systems |
US10046859B2 (en) | 2015-01-14 | 2018-08-14 | Goodrich Actuation Systems Limited | Anti-icing systems |
RU2714330C2 (en) * | 2015-01-14 | 2020-02-14 | Гудрич Эктьюэйшен Системз Лимитед | Bleed air pressure control system for aircraft anti-icing system, aircraft engine nacelle anti-icing system and air bleed control method in anti-icing system |
EP3259508A4 (en) * | 2015-02-16 | 2018-10-03 | Dukes Aerospace Inc. | Redundant valve system |
EP3266712A1 (en) * | 2016-07-06 | 2018-01-10 | United Technologies Corporation | Nacelle anti ice system |
US10450955B2 (en) | 2016-07-06 | 2019-10-22 | United Technologies Corporation | Nacelle anti ice system |
US11060454B2 (en) | 2016-07-06 | 2021-07-13 | Raytheon Technologies Corporation | Method of regulating air pressure in anti-icing system |
EP4350128A1 (en) * | 2022-10-03 | 2024-04-10 | Microtecnica S.r.l. | Pressure regulating shut-off valve |
Also Published As
Publication number | Publication date |
---|---|
DE2007256A1 (en) | 1970-09-03 |
FR2035639A5 (en) | 1970-12-18 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PLE | Entries relating assignments, transmissions, licences in the register of patents | ||
PE20 | Patent expired after termination of 20 years |