Abstract A gas turbine engine includes, in flow series arrangement, a mixer, a compressor, a first flow path of a recuperator, a combustor, a turbine and a second flow path of said recuperator; and a bypass conduit between said turbine and said mixer. A valve is disposed in the conduit and is controlled by a temperature sensor mounted to sense compressor inlet air temperature. The sensor has a set point temperature that corresponds with optimum emissions from the engine. When the sensed temperature drops below the set point temperature the valve opens and hot air from the turbine flows to the mixer where it heats the air entering the compressor. A method for operating a gas turbine engine with preselected emissions over a range of ambient conditions is also disclosed.
A gas turbine engine comprising, in flow series arrangement, a mixer, a compressor, a first flow path of a recuperator, a combustor, a turbine and a second flow path of said recuperator; and a bypass conduit between said turbine and said mixer.
Claim 2
Dependent Claim
42 words
A gas turbine engine comprising, in flow series arrangement, a mixer, a compressor, a first flow path of a recuperator, a combustor, a turbine and a second flow path of said recuperator; and a bypass conduit between said turbine and said mixer.
Claim 3
Dependent Claim
15 words
The gas turbine engine of claim 1 further comprising a valve disposed in said conduit.
Claim 4
Dependent Claim
25 words
The gas turbine engine of claim 2 further comprising a temperature sensor mounted to sense compressor inlet air temperature and having a set point temperature.
Claim 5
Dependent Claim
29 words
The gas turbine engine of claim 3 wherein said temperature sensor is configured so that when the sensed temperature is below the set point temperature the valve is open.
Claim 6
Dependent Claim
29 words
The gas turbine engine of claim 3 wherein said valve is controlled by an electronic control unit of the engine in response to a signal from said temperature sensor.
Claim 7
Dependent Claim
20 words
The gas turbine engine of claim 2 wherein said valve is proportionately controlled as a function of compressor inlet temperature.