IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0353097
(2006-02-14)
|
등록번호 |
US-7841185
(2011-01-31)
|
우선권정보 |
GB-0504272.6(2005-03-02) |
발명자
/ 주소 |
- Richards, Martyn
- Howarth, Nicholas
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
7 인용 특허 :
6 |
초록
▼
Disparities between optimum engine thrust for aircraft operation and power necessary to drive an ancillary machine such an electrical power generator can cause problems within a turbine engine. Clearly, it is necessary to continue developing sufficient electrical power for control and other systems
Disparities between optimum engine thrust for aircraft operation and power necessary to drive an ancillary machine such an electrical power generator can cause problems within a turbine engine. Clearly, it is necessary to continue developing sufficient electrical power for control and other systems within an aircraft despite aircraft thrust requirements. Previously, some compressed air flow has been bypassed in order to maintain compressor stability, but unfortunately such bypass systems within turbine engines can have a thrust recovery regime such that there is excess thrust in comparison with that actually necessary. In accordance with the present invention, a proportion of the compressed air flow is bled directly through a bleed path to an exhaust nozzle 104 of an engine such that the compressor core can continue to provide work to drive an ancillary machine whilst engine thrust is limited to that actually required, achieving a significant saving in terms of fuel consumption and wear and tear upon brakes, etc under low power operation.
대표청구항
▼
We claim: 1. A method of providing propulsive thrust to an aircraft from a gas turbine engine comprising, in axial flow series: a propulsive fan; a compressor; a combustor; a turbine; a final turbine, wherein said propulsive fan produces, during use, a first air flow passing into said compressor an
We claim: 1. A method of providing propulsive thrust to an aircraft from a gas turbine engine comprising, in axial flow series: a propulsive fan; a compressor; a combustor; a turbine; a final turbine, wherein said propulsive fan produces, during use, a first air flow passing into said compressor and a second air flow which provides propulsive thrust, and wherein said compressor is driven by said turbine via a compressor core shaft and said propulsive fan is driven by said final turbine via a shaft; and an exhaust nozzle through which hot combustion gases are exhausted to provide additional propulsive thrust, the method comprising: operating the gas turbine engine to produce a first propulsive thrust; driving an electrical generator by work taken from the compressor core shaft; bleeding compressed air from the compressor to the exhaust nozzle to provide a reduced propulsive thrust, provided by reducing said second air flow being delivered from said propulsive fan, and maintain the work; and using a controller to determine a proportion of compressed air to bleed to provide the reduced propulsive thrust and maintain the work. 2. A method according to claim 1, wherein method comprises the step of bleeding the compressor during any one of the engine descent, ground idle and lower thrust conditions. 3. A method according to claim 1, wherein the engine comprises a control valve provided to control the proportion of compressed air bled from the compressor. 4. A method of providing propulsive thrust to an aircraft from a gas turbine engine comprising, in axial flow series: a propulsive fan; a compressor; a combustor; a turbine; a final turbine, wherein said propulsive fan produces, during use, a first air flow passing into said compressor and a second air flow which provides propulsive thrust, and wherein said compressor is driven by said turbine via a compressor core shaft and said propulsive fan is driven by said final turbine via a shaft; and an exhaust nozzle through which hot combustion gases are exhausted to provide additional propulsive thrust, the method comprising: operating the gas turbine engine to produce a first propulsive thrust; driving an electrical generator by work taken from the compressor core shaft; bleeding compressed air from the compressor to the exhaust nozzle to provide a reduced propulsive thrust, provided by reducing said second air flow being delivered from said propulsive fan, during any one or more of descent, approach or landing of the aircraft or idling of the engine and maintain the work; and using a controller to determine an amount of reduced fuel flow to the combustor and determine a proportion of compressed air to bleed to provide the reduced propulsive thrust and maintain the work. 5. A method of providing propulsive thrust to an aircraft from a gas turbine engine comprising, in axial flow series: a propulsive fan; a compressor; a combustor; a turbine; a final turbine, wherein said propulsive fan produces, during use, a first air flow passing into said compressor and a second air flow which provides propulsive thrust, and wherein said compressor is driven by said turbine via a compressor core shaft and said propulsive fan is driven by said final turbine via a shaft; and an exhaust nozzle through which hot combustion gases are exhausted to provide additional propulsive thrust, the method comprising: operating the gas turbine engine to produce a first propulsive thrust; driving an electrical generator by work taken from the compressor core shaft; bleeding compressed air from the compressor to the exhaust nozzle to provide a reduced propulsive thrust, provided by reducing said second air flow being delivered from said propulsive fan, and maintain the work; and using a controller to determine an amount of fuel flow to the combustor and determine a proportion of compressed air to bleed to provide the reduced propulsive thrust and maintain the work. 6. A method according to claim 5, wherein the reduced propulsive thrust is provided during idle or any one or more of descent, approach or landing of the aircraft. 7. A method according to claim 1, wherein the controller receives signals indicative of air speed, ground speed, and vertical speed of the aircraft and adjusts a fuel flow to the combustor and determines a proportion of air to bleed based on the input of the signals. 8. A method according to claim 1, wherein the controller receives signals indicative of air speed, ground speed, and vertical speed of the aircraft and adjusts a fuel flow to the combustor and determines a proportion of air to bleed based on the input of the signals to both maintain the work capacity and provide a steeper descent to reduce altitude in a given horizontal constraint. 9. A method according to claim 4, wherein the controller receives signals indicative of air speed, ground speed, and vertical speed of the aircraft and adjusts the fuel flow to the combustor and determines a proportion of air to bleed based on the input of the signals. 10. A method according to claim 4, wherein the controller receives signals indicative of air speed, ground speed, and vertical speed of the aircraft and adjusts the fuel flow to the combustor and determines a proportion of air to bleed based on the input of the signals to both maintain the work capacity and provide a steeper descent to reduce altitude in a given horizontal constraint. 11. A method according to claim 5, wherein the controller receives signals indicative of air speed, ground speed, and vertical speed of the aircraft and adjusts the fuel flow to the combustor and determines a proportion of air to bleed based on the input of the signals. 12. A method according to claim 5, wherein the controller receives signals indicative of air speed, ground speed, and vertical speed of the aircraft and adjusts the fuel flow to the combustor and determines a proportion of air to bleed based on the input of the signals to both maintain the work capacity and provide a steeper descent to reduce altitude in a given horizontal constraint.
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