GB2421281A - Starting and anti-icing in a gas turbine engine - Google Patents
Starting and anti-icing in a gas turbine engine Download PDFInfo
- Publication number
- GB2421281A GB2421281A GB0427676A GB0427676A GB2421281A GB 2421281 A GB2421281 A GB 2421281A GB 0427676 A GB0427676 A GB 0427676A GB 0427676 A GB0427676 A GB 0427676A GB 2421281 A GB2421281 A GB 2421281A
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- GB
- United Kingdom
- Prior art keywords
- air
- gas turbine
- duct
- turbine engine
- starter
- 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.)
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- 239000007858 starting material Substances 0.000 claims abstract description 96
- 238000011144 upstream manufacturing Methods 0.000 claims description 20
- 230000005540 biological transmission Effects 0.000 claims description 8
- 230000001419 dependent effect Effects 0.000 claims 5
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000001141 propulsive effect Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000009970 fire resistant effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- 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
-
- 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
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
-
- 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
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/275—Mechanical drives
- F02C7/277—Mechanical drives the starter being a separate turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Supercharger (AREA)
Abstract
A gas turbine engine 10 includes an air intake 42 having a hollow annular wall 44 defining an annular cavity 46. The gas turbine engine 10 includes a thermal anti-icing arrangement 48, associated with the air intake 42, and a starter arrangement 50. A circumferentially extending air transfer duct 52 is located within the cavity 46 defined by the wall 44 of the air intake 42, and has a first operating condition in which the duct 52 is operable to transfer air to the starter arrangement 50, and a second operating condition in which the duct 52 is operable to transfer air to the thermal anti-icing arrangement 48. The air transfer duct 52 may be located between a forward bulkhead 60 and a rear bulkhead 62. The air intake 42 may be removeably mounted on the engine 10 by releaseable attachment means.
Description
Engine Air Intake for Gas Turbine Engines
The present invention relates to an engine air intake for use with a gas turbine engine. The invention also relates to a gas turbine engine including an engine air intake.
Conventional gas turbine engines include an air starter arrangement to enable engine starting and a thermal antiicing arrangement to prevent icing of the engine air intake, for example during aircraft descent.
The air starter arrangement includes an air starter duct which extends from an upper region of the engine fancase, around approximately half of its circumference, to a lower region of the fancase where it is connected to a starter. The starter can receive air, via the starter air duct, from any one of a number of sources including an external ground supply, an auxiliary power unit on board an aircraft or by cross-feed from a running gas turbine engine.
The thermal anti-icing arrangement includes an antiicing duct which conventionally extends along the lower region of the engine fancase towards the front of the fancase. The anti-icing duct is connected at the front of the fancase in use to a duct in the engine air intake and conveys anti-icing air from the compressor into a cavity in the air intake to prevent formation of ice on the air intake.
According to a first aspect of the present invention, there is provided a gas turbine engine including:
an air intake comprising a hollow annular wall defining an annular cavity; a thermal anti-icing arrangement associated with the air intake; and a starter arrangement, wherein the gas turbine engine includes a circumferentially extending air transfer duct located within the cavity defined by the wall of the air intake, the air transfer duct having a first operating condition in which the duct is operable to transfer air to the starter arrangement and a second operating condition in which the duct is operable to transfer air to the thermal anti-icing arrangement.
According to a second aspect of the present invention, there is provided an engine air intake for use with a gas turbine engine including a starter arrangement, the engine air intake comprising a hollow annular wall defining an annular cavity, and a thermal anti-icing arrangement associated with the air intake, wherein the engine air intake includes a circumferentially extending air transfer duct located within the cavity defined by the wall of the air intake, the air transfer duct having a first operating condition in which the duct is operable to transfer air in use to the starter arrangement, and a second operating condition in which the duct is operable to transfer air in use to the thermal anti-icing arrangement.
The air transfer duct may include an inlet and an outlet, and may extend circumferentially around the cavity between the inlet and the outlet. The inlet is preferably located in an upper region of the engine. The outlet is preferably located in a lower region of the engine.
The hollow annular wall may include a generally cylindrical outer part and a generally cylindrical inner part, and the outer and inner parts may be joined together at an upstream end of the engine by a curved annular nose part.
The air intake may comprise a forward bulkhead and a rear bulkhead extending between the outer and inner parts to divide the annular cavity. The rear bulkhead may provide a firewall and the air transfer duct may be located within the cavity between the front and rear bulkheads. The air transfer duct may be mounted on the rear bulkhead on an upstream side of the rear bulkhead.
The air outlet may be configured to transfer air to the starter arrangement when the air transfer duct is in the first operating condition, and may be configured to transfer air to the thermal anti-icing arrangement when the air transfer duct is in the second operating condition.
The starter arrangement may include a starter motor, a starter air duct for transferring air from the air transfer duct to the starter motor, and a starter air valve. The starter air valve may be selectively operable between an open condition to allow transmission of air from the air transfer duct to the starter air duct, and a closed condition to prevent transmission of air from the air transfer duct to the starter air duct. The thermal antiicing arrangement may include an anti-icing duct and an anti-icing valve. The anti-icing valve may be operable between an open condition to allow transmission of air from the air transfer duct to the anti-icing duct, and a closed condition to prevent transmission of air from the air transfer duct to the anti-icing duct.
When the gas turbine engine is configured such that the air transfer duct is in the first operating condition, the starter air valve may be in the open condition and the antiicing valve may be in the closed condition. When the gas turbine engine is configured such that the air transfer duct is in the second operating condition, the starter air valve may be in the closed condition and the anti-icing valve may be in the open condition.
The air outlet may comprise two outlet ports. Each of the starter air valve and the anti-icing valve may be connected to a respective outlet port. The outlet ports may be located on opposite sides of the air transfer duct.
The air transfer duct may be configured to receive air from a starter air supply when the gas turbine engine is configured such that the air transfer duct is in the first operating condition. The air transfer duct may be configured to receive air from an anti-icing air supply when the gas turbine engine is configured such that the air transfer duct is in the second operating condition. When the gas turbine engine is configured such that the air transfer duct is in the first operating condition, the starter air supply may be activated and the anti-icing air supply may be deactivated. When the gas turbine engine is configured such that the air transfer duct is in the second operating condition, the starter air supply may be deactivated and the anti-icing air supply may be activated.
The starter air supply and the anti-icing air supply may provide air to the air transfer duct via the air inlet. The air inlet may comprise an inlet port which may provide air from either the starter air supply or the anti-icing air supply to the air transfer duct.
The gas turbine engine may include an air inlet duct which may transfer air from either the starter air supply or the anti-icing air supply to the air inlet. The air inlet duct may extend from the air inlet in a downstream direction of the engine.
The thermal anti-icing arrangement may be located within the cavity defined by the hollow annular wall of the air intake. The anti-icing duct may extend axially through the cavity in an upstream direction towards the curved annular nose part, and may project through the forward bulkhead.
The engine air intake may be removably mountable on the engine and may include an attachment arrangement to provide for removable mounting. The attachment arrangement may include releasable attachment means. The releasable attachment means may be operable respectively between the air inlet and the air inlet duct, and the air outlet and the starter air valve.
An embodiment of the present invention will now be described by way of example only and with reference to the accompanying drawings, in which:- Fig. 1 is a diagrammatic cross-sectional view of a part of a gas turbine engine; and Fig. 2 is a detailed diagrammatic view of an upstream end of the gas turbine engine of Fig. 1.
Referring to Fig. 1, there is shown a gas turbine engine 10 comprising, in axial flow series, an air inlet 24, surrounded by an annular air intake 42, a propulsive fan 26, an intermediate pressure compressor 28, a high pressure compressor 30, combustion equipment 32, a high pressure turbine 34, an intermediate pressure turbine 36, a low pressure turbine 38 and an exhaust nozzle 40.
The gas turbine engine 10 works in a conventional manner so that air entering the air inlet 24 is accelerated by the fan 26 which produce two air flows: a first air flow into the intermediate pressure compressor 28 and a second air flow which provides propulsive thrust. The intermediate pressure compressor 28 compresses the air flow directed into it before delivering that air to the high pressure compressor 30 where further compression takes place.
The compressed air exhausted from the high pressure compressor 30 is directed into the combustion equipment 32 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 34, 36 and 38 before being exhausted through the nozzle 40 to provide additional propulsive thrust. The high, intermediate and low pressure turbines 34, 36 and 38 respectively drive the high and intermediate pressure compressors 30 and 28, and the fan 26 by suitable interconnecting shafts.
Referring to Fig. 2, the air intake 42 has a hollow annular wall 44 defining an annular cavity 46, and the gas turbine engine 10 includes a thermal anti-icing arrangement, generally designated 48, associated with the air intake 42, and a starter arrangement, generally designated 50. The gas turbine engine 10 includes a circumferentially extending air transfer duct 52 located within the cavity 46 defined by the wall 44 of the air intake 42, the air transfer duct 52 having a first operating condition in which the duct 52 is operable to transfer air to the starter arrangement 50, and a second operating condition in which the duct 52 is operable to transfer air to the thermal anti-icing arrangement 48.
In more detail, the hollow annular wall 44 of the air intake 42 includes a generally cylindrical outer part 54 and a generally cylindrical inner part 56, the inner and outer parts 54, 56 being joined together at an upstream end of the engine 10 by a curved annular nose part 58, commonly referred to as the intake lipskin. The annular cavity 46 is divided into a number of portions by a forward bulkhead 60 and a rear bulkhead 62, each of which extend circumferentially around the cavity 46 and between the outer and inner parts 54, 56 of the wall 44. The rear bulkhead 62 is formed of a fire resistant material, such as titanium, and thereby acts as a firewall such that the portion of the cavity 46 upstream of the rear bulkhead 62 is a zone which is not at risk from fire, conventionally known as a 'no fire zone'.
The air transfer duct 52 extends circumferentially through the cavity 46 from an upper region of the engine 10, around approximately half of the circumference of the engine air intake 42, to a lower region of the engine 10. The air transfer duct 52 is located within the cavity 46 upstream of the rear bulkhead 62 between the forward and rear bulkheads 60, 62 in the no fire zone, and in a preferred embodiment is mounted on the rear bulkhead 62 on the upstream side thereof.
The air transfer duct 52 includes an air inlet 64 in the form of an inlet port 68 in the upper region of the engine 10, and an air outlet 66 comprising two oppositely directed outlet ports 70, 72 on opposite sides of the air transfer duct 52 in the lower region of the engine 10.
The air inlet port 68 is releasably connected via a quick attach/detach mechanism to an air inlet duct 74 which extends along the upper region of the engine 10 from the air inlet port 68 in a downstream direction. The air inlet duct 74 is configured to convey air to the air inlet 64 from either a starter air supply, for example an external ground supply (not shown), or from an anti-icing air supply, such as the compressor 14, as will be described in detail hereinafter.
The anti-icing arrangement 48 is located within the hollow cavity 46 and comprises an anti-icing valve 76 connected to the outlet port 70 on the upstream side of the air transfer duct 52, and an anti-icing duct 78 connected at one end to the anti-icing valve 76 and extending in an upstream direction through the forward bulkhead 60 of the cavity 46 towards the curved nose part 58. The anti-icing duct 78 includes an outlet 84 at its upstream end to convey anti-icing air to the portion of the cavity 46 upstream of the forward bulkhead 60 adjacent to the curved nose part 58.
The anti-icing valve 76 is operable between an open condition to permit the transfer of anti-icing air from the air transfer duct 52 to the anti-icing duct 78, and a closed condition in which the transfer of anti-icing air is prevented. This is described in detail below.
The starter arrangement 50 includes a starter air valve 80, a starter 16 and a starter air duct 82 which extends between, and is connected to, both the starter air valve 80 and the starter 16. The starter air valve 80, starter 16 and starter air duct 82 are all provided on board the gas turbine engine 10, and the outlet port 72 on the downstream side of the air transfer duct 52 is releasably connected to the starter air valve 80 via a quick attach/detach mechanism. The starter air duct 82 is configured to transfer starter air, in use, to the starter 16 which in turn is operable to start the gas turbine engine 10. The starter air valve 80 is operable between an open condition to permit the transfer of starter air from the air transfer duct 52 to the starter air duct 82, and a closed condition in which the transfer of starter air is prevented. This is described in detail below.
When engine starting is desired, the engine 10 is configured so that the air transfer duct 52 is in the first operating condition. When in the first operating condition, the starter air valve 80 is set to the open condition to allow the transfer of starter air to the starter air duct 82, and the anti-icing valve 76 is set to the closed condition to prevent the transfer of starter air to the anti-icing duct 78. The starter air supply is then activated and starter air is conveyed along the air inlet duct 74 to the air inlet 64 of the air transfer duct 52. The starter air is then conveyed through the air transfer duct 52 to the air outlet 66, and due to the condition settings of the anti-icing and starter air valves 76, 80, the starter air travels along the starter air duct 82 to the starter 16.When engine starting is completed and the engine 10 is running, the starter air supply is deactivated and the starter air valve 80 is closed.
When anti-icing of the air intake 42 is required, the engine 10 is configured so that the air transfer duct 52 is in the second operating condition. When in the second operating condition, the anti-icing valve 76 is set to the open condition to enable the transfer of anti-icing air to the anti-icing duct 78, and the starter air valve 80 is set to the closed condition to prevent the transfer of antiicing air to the starter air duct 82.
Anti-icing air is bled from the intermediate or high pressure compressor 14, and is conveyed along the inlet duct 74 to the air inlet 64. The anti-icing air is then conveyed through the air transfer duct 52 to the air outlet 66, and due to the condition settings of the anti-icing and starter air valves 76, 80, the anti-icing air travels along the anti-icing duct 82 to the outlet 84. The anti-icing air is then caused to flow circumferentially around the portion of the cavity 46 upstream of the forward bulkhead 60 so that ice formation on the outer surface of the curved nose part 58 is prevented.
When anti-icing of the engine air intake 42 is completed, the anti-icing air supply is deactivated and the anti-icing valve 76 is closed to prevent the further transfer of air into the anti-icing duct 78.
There is thus provided a gas turbine engine 10 including an engine air intake 42 which includes an air transfer duct 52 for conveying air to either a starter arrangement 50 or a thermal anti-icing arrangement 48. Due to the location of the air transfer duct 52 in the cavity 46 upstream of the rear bulkhead 62 in the no fire zone, lighter and/or lower cost materials may be used in the manufacture of the air transfer duct 52 than are currently used in the manufacture of an air starter duct in a conventional gas turbine engine.
The invention also offers the advantage that the antiicing duct 78 is fully integrated into the engine air intake 42 and receives anti-icing air from the air transfer duct 52. Accordingly, the anti-icing duct 78 does not extend along the lower region of the engine 10, thus reducing the amount of ducting used and providing a weight reduction.
This also provides more space in the lower region of the engine 10.
Integration of the air transfer duct 52 into the engine air intake 42 also facilitates engine transportation, since the starter air duct of a conventional gas turbine engine may need to be removed to enable engine transportation, and must subsequently be re-fitted to the engine when it arrives at its destination for mounting on an aircraft. With the present invention, mounting of the engine air intake 42 provides for simultaneous mounting of the air transfer duct 52.
Although embodiments of the invention have been described in the preceding paragraphs with reference to various examples, it should be appreciated that various modifications to the examples given may be made without departing from the scope of the present invention, as claimed. For example, the air transfer duct 52 may be located at any position within the cavity 46, provided that it is located upstream of the rear bulkhead 62. The air transfer duct 52 may be formed integrally with the rear bulkhead 62.
Whilst endeavouring in the foregoing specification to draw attention to those features of the invention believed to be of particular importance, it should be understood that the Applicant claims protection in respect of any patentable feature or combination of features hereinbefore referred to and/or shown in the drawings, whether or not particular emphasis has been placed thereon.
Claims (37)
1. A gas turbine engine including: an air intake comprising a hollow annular wall defining an annular cavity; a thermal anti-icing arrangement associated with the air intake; and a starter arrangement, wherein the gas turbine engine includes a circumferentially extending air transfer duct located within the cavity defined by the wall of the air intake, the air transfer duct having a first operating condition in which the duct is operable to transfer air to the starter arrangement and a second operating condition in which the duct is operable to transfer air to the thermal anti-icing arrangement.
2. A gas turbine engine according to claim 1, wherein the air transfer duct includes an inlet and an outlet, and extends circumferentially around the cavity between the inlet and the outlet, the inlet being located in an upper region of the engine and the outlet being located in a lower region of the engine.
3. A gas turbine engine according to claim 1 or claim 2, wherein the hollow annular wall includes a generally cylindrical outer part and a generally cylindrical inner part, the outer and inner parts being joined together at an upstream end of the engine by a curved annular nose part.
4. A gas turbine engine according to any of the preceding claims, wherein the air intake comprises a forward bulkhead and a rear bulkhead extending between the outer and inner parts to divide the annular cavity, the rear bulkhead providing a firewall and the air transfer duct being located within the cavity between the front and rear bulkheads.
5. A gas turbine engine according to claim 4, wherein the air transfer duct is mounted on the rear bulkhead on an upstream side of the rear bulkhead.
6. A gas turbine engine according to any of claims 2 to 5, wherein the air outlet is configured to transfer air to the starter arrangement when the air transfer duct is in the first operating condition and to transfer air to the thermal anti-icing arrangement when the air transfer duct is in the second operating condition.
7. A gas turbine engine according to any of the preceding claims, wherein the starter arrangement includes a starter motor, a starter air duct for transferring air from the air transfer duct to the starter motor, and a starter air valve selectively operable between an open condition to allow transmission of air from the air transfer duct to the starter air duct, and a closed condition to prevent transmission of air from the air transfer duct to the starter air duct.
8. A gas turbine engine according to any of the preceding claims, wherein the thermal anti-icing arrangement includes an anti-icing duct and an anti-icing valve operable between an open condition to allow transmission of air from the air transfer duct to the anti-icing duct, and a closed condition to prevent transmission of air from the air transfer duct to the anti-icing duct.
9. A gas turbine engine according to claim 8 when dependent on claim 7, wherein when the gas turbine engine is configured such that the air transfer duct is in the first operating condition, the starter air valve is in the open condition and the anti-icing valve is in the closed condition.
10. A gas turbine engine according to claim 9 or claim 8 when dependent on claim 7, wherein when the gas turbine engine is configured such that the air transfer duct is in the second operating condition, the starter air valve is in the closed condition and the anti-icing valve is in the open condition.
11. A gas turbine engine according to any of claims 7 to 10 when dependent on claim 2, wherein the air outlet comprises two outlet ports, and each of the starter air valve and the anti-icing valve is connected to a respective outlet port.
12. A gas turbine engine according to claim 11, wherein the outlet ports are located on opposite sides of the air transfer duct.
13. A gas turbine engine according to any of the preceding claims, wherein the air transfer duct is configured to receive air from a starter air supply when the gas turbine engine is configured such that the air transfer duct is in the first operating condition, and from an anti-icing air supply when the gas turbine engine is configured such that the air transfer duct is in the second operating condition.
14. A gas turbine engine according to claim 13, wherein when the gas turbine engine is configured such that the air transfer duct is in the first operating condition, the starter air supply is activated and the anti-icing air supply is deactivated.
15. A gas turbine engine according to claim 13 or claim 14, wherein when the gas turbine engine is configured such that the air transfer duct is in the second operating condition, the starter air supply is deactivated and the anti-icing air supply is activated.
16. A gas turbine engine according to any of claims 13 to
15 when dependent on claim 2, wherein the starter air supply and the anti-icing air supply provide air to the air transfer duct via the air inlet.
17. A gas turbine engine according to claim 16, wherein the air inlet comprises an inlet port for providing air from either the starter air supply or the anti-icing air supply to the air transfer duct.
18. A gas turbine engine according to claim 16 or claim 17, wherein the gas turbine engine includes an air inlet duct for transferring air from either the starter air supply or the anti-icing air supply to the air inlet, the air inlet duct extending from the air inlet in a downstream direction of the engine.
19. A gas turbine engine according to any of the preceding claims, wherein the thermal anti-icing arrangement is located within the cavity defined by the hollow annular wall of the air intake.
20. A gas turbine engine according to any of claims 8 to 19 when dependent on claim 3, wherein the anti-icing duct extends axially through the cavity in an upstream direction towards the curved nose part, and projects through the forward bulkhead.
21. A gas turbine engine according to any of the preceding claims, wherein the engine air intake is removably mountable on the engine and includes an attachment arrangement to provide for removable mounting.
22. A gas turbine engine according to claim 21, wherein the attachment arrangement includes releasable attachment means operable respectively between the air inlet and the air inlet duct, and the air outlet and the starter air valve.
23. An engine air intake for use with a gas turbine engine including a starter arrangement, the engine air intake comprising a hollow annular wall defining an annular cavity, and a thermal anti-icing arrangement associated with the air intake, wherein the engine air intake includes a circumferentially extending air transfer duct located within the cavity defined by the wall of the air intake, the air transfer duct having a first operating condition in which the duct is operable to transfer air in use to the starter arrangement, and a second operating condition in which the duct is operable to transfer air in use to the thermal antiicing arrangement.
24. An engine air intake according to claim 23, wherein the air transfer duct includes an inlet and an outlet and extends circumferentially around the cavity between the inlet and the outlet, the inlet being located in use in an upper region of the engine and the outlet being located in use in a lower region of the engine.
25. An engine air intake according to claim 23 or claim 24, wherein the hollow annular wall includes a generally cylindrical outer part and a generally cylindrical inner part, the outer and inner parts being joined together at an in use upstream end by a curved annular nose part.
26. An engine air intake according to claim 25, wherein the engine air intake comprises a forward bulkhead and a rear bulkhead extending between the outer and inner parts to divide the annular cavity, the rear bulkhead providing a firewall and the air transfer duct being located within the cavity between the front and rear bulkheads.
27. An engine air intake according to claim 26, wherein the air transfer duct is mounted on the rear bulkhead on an in use upstream side of the rear bulkhead.
28. An engine air intake according to any of claims 24 to
27, wherein the air outlet comprises two outlet ports, one of said outlet ports being configured for connection to a starter air valve and the other of said ports being connected to an anti-icing valve.
29. An engine air intake according to claim 28, wherein the outlet ports are located on opposite sides of the air transfer duct.
30. An engine air intake according to any of claims 23 to
29, wherein the air transfer duct is configured to receive air from a starter air supply when the air transfer duct is in the first operating condition in use, and from an antiicing air supply when the air transfer duct is in the second operating condition in use.
31. An engine air intake according to claim any of claims
24 to 30, wherein the air inlet comprises an inlet port for providing air in use from either the starter air supply or the anti-icing air supply to the air transfer duct.
32. An engine air intake according to any of claims 23 to
31, wherein the thermal anti-icing arrangement is located within the cavity defined by the hollow annular wall of the air intake.
33. An engine air intake according to any of claims 23 to
32, wherein the engine air intake is removably mountable on an engine and includes an attachment arrangement to provide for removable mounting.
34. An engine air intake according to claim 33, wherein the attachment arrangement comprises releasable attachment means operable in use respectively between the air inlet and an air inlet duct of the gas turbine engine, and the air outlet and the starter air valve of the gas turbine engine.
35. A gas turbine engine substantially as hereinbefore described with reference to and/or as shown by the accompanying drawings.
36. An engine air intake for use with a gas turbine engine substantially as hereinbefore described with reference to and/or as shown the accompanying drawings.
37. Any novel subject matter or combination including novel subject matter disclosed herein, whether or not within the scope of or relating to the same invention as any of the preceding claims.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0427676A GB2421281A (en) | 2004-12-16 | 2004-12-16 | Starting and anti-icing in a gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0427676A GB2421281A (en) | 2004-12-16 | 2004-12-16 | Starting and anti-icing in a gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB0427676D0 GB0427676D0 (en) | 2005-01-19 |
| GB2421281A true GB2421281A (en) | 2006-06-21 |
Family
ID=34090231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0427676A Withdrawn GB2421281A (en) | 2004-12-16 | 2004-12-16 | Starting and anti-icing in a gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2421281A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB889305A (en) * | 1959-11-26 | 1962-02-14 | Rolls Royce | Gas turbine engine |
| GB2072268A (en) * | 1980-03-20 | 1981-09-30 | Gen Electric | Fuel efficiency of a gas turbine engine |
| GB2242235A (en) * | 1990-03-06 | 1991-09-25 | Gen Electric | Aircraft engine bleed system |
| EP0459816A1 (en) * | 1990-06-01 | 1991-12-04 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
-
2004
- 2004-12-16 GB GB0427676A patent/GB2421281A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB889305A (en) * | 1959-11-26 | 1962-02-14 | Rolls Royce | Gas turbine engine |
| GB2072268A (en) * | 1980-03-20 | 1981-09-30 | Gen Electric | Fuel efficiency of a gas turbine engine |
| GB2242235A (en) * | 1990-03-06 | 1991-09-25 | Gen Electric | Aircraft engine bleed system |
| EP0459816A1 (en) * | 1990-06-01 | 1991-12-04 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0427676D0 (en) | 2005-01-19 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |