초록 ▼

A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to

A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

대표청구항 ▼

1. A method comprising: operating a first aircraft engine and a second aircraft engine to produce propulsive thrust to power a multi-engine aircraft to a flight condition, the second aircraft engine being a gas turbine engine having a compressor, combustor, and turbine;actuating a valve to open a fl

1. A method comprising: operating a first aircraft engine and a second aircraft engine to produce propulsive thrust to power a multi-engine aircraft to a flight condition, the second aircraft engine being a gas turbine engine having a compressor, combustor, and turbine;actuating a valve to open a flow path from a source of compressed working fluid on board the multi-engine aircraft to permit passage of a compressed working fluid from the source of compressed working fluid to the combustor of the gas turbine engine as a result of a degraded performance of the first aircraft engine during a portion of the operating, the source of compressed working fluid being a pressurized tank;conveying the compressed working fluid, the compressed working fluid being air, from the source of compressed working fluid to the combustor of the gas turbine engine; andproducing a propulsive thrust increase from the second aircraft engine as a result of the conveying the fluid;wherein the multi-engine aircraft includes a controller structured to actuate the valve in response to the first aircraft engine failing to provide a commanded level of thrust as a result of the degraded performance of the first aircraft engine; andwherein a pump provides the compressed working fluid to the pressurized tank, the pump being driven via a gearing powered by the gas turbine engine. 2. The method of claim 1, further comprising introducing the compressed working fluid into the compressor of the gas turbine engine. 3. The method of claim 2, further comprising monitoring the first aircraft engine and detecting the degraded performance of the first aircraft engine. 4. The method of claim 3, wherein the actuating the valve in response to the degraded performance comprises the controller commanding the valve to be actuated when the monitoring detects the degraded performance. 5. An apparatus comprising: a multi-engine aircraft including a first engine and a gas turbine engine having a compressor, combustor, and turbine;a source of compressed working fluid coupled with the multi-engine aircraft and operable to dispense compressed working fluid to the gas turbine engine;a valve coupled with the source of compressed working fluid and operable to permit passage of the compressed working fluid to the combustor of the gas turbine engine when the valve is operated; andwherein the valve is actuated to increase a mass flow through the gas turbine engine to boost power of the gas turbine engine during operation of the gas turbine engine,wherein the apparatus further includes a controller structured to actuate the valve in response to the first engine failing to provide a commanded level of thrust,wherein the compressed working fluid is air,wherein the source of compressed working fluid is a pressurized tank, andwherein the apparatus further includes a pump driven via a gearing powered by the gas turbine engine and the pump is configured to provide the compressed working fluid to the pressurized tank. 6. The apparatus of claim 5, wherein the controller is further structured to actuate the valve in response to receiving a signal from a pilot interface. 7. The apparatus of claim 5, wherein the controller is operable to cause a delivery of a first quantity of fuel to be burned in the combustor of the gas turbine engine before the valve is actuated and to further cause a delivery of a second quantity of fuel to be burned in the combustor of the gas turbine engine after the valve is actuated, wherein the second quantity of fuel is greater than the first quantity of fuel. 8. An apparatus comprising: an aircraft having a first engine and a second engine, the first engine and the second engine operable to produce power for the aircraft by combusting a mixture of a compressed working fluid and a fuel;an engine power supplement device configured to increase the power from the first engine, the engine power supplement device including a vessel having a compressed supplement fluid, the vessel configured to conduct the compressed supplement fluid to the first engine; anda controller configured to instruct the engine power supplement device to provide the compressed supplement fluid to the first engine to supplement the compressed working fluid in response to the second engine being in a degraded operating state,wherein the compressed supplement fluid is air, the apparatus further including a pump operable to pressurize the air to create the compressed supplement fluid and convey the compressed supplement fluid toward the vessel,wherein the pump is configured to be drive via a gearing, andwherein the gearing is configured to be driven by each of the first engine and the second engine. 9. The apparatus of claim 8, wherein the aircraft includes a flow path from the vessel to the first engine, the flow path providing the compressed supplement fluid to a combustor in which the mixture of the compressed working fluid and the fuel is combusted. 10. The apparatus of claim 9, wherein the first engine includes a port in an axially forward portion of the combustor.