Mounting of fluidic temperature sensor in gas turbine engines

Claim 2

A fluidic temperature sensor assembly for a gas turbine engine, said assembly comprising: an aerodynamic vane extending across a hot fluid stream in said gas turbine; means for providing a cooling-air passageway through said vane; a fluidic oscillator having an oscillating chamber positioned in said cooling passageway means and having an inlet extending to an upstream portion of said vane and an outlet extending to a discharge point at a pressure lower than the pressure at said inlet; and means for sensing the pressure oscillations in said fluidic oscillator as a function of the temperature of said fluid stream.

Claim 3

A fluidic temperature sensor as in claim 1 wherein said aerodynamic vane comprises a vane of a plurality of vanes comprising an inlet nozzle for a turbine assembly, whereby said fluidic temperature sensor senses turbine inlet temperature.

Claim 4

A fluidic temperature sensor as in claim 2 wherein said turbine nozzle vanes are shaped to provide converging, diverging passageways through said turbine nozzle to provide a choked condition at a throat portion and wherein said inlet extends to the leading edge of said vane and said outlet extends to the throat portion of said turbine nozzle, thereby providing said low-pressure discharge.

Claim 5

A fluidic temperature sensor as in claim 2 wherein said outlet extends to a point downstream of said turbine assembly.

Claim 6

A fluidic temperature sensor as in claim 2 wherein the means for sensing the pressure oscillations in said chamber comprises: an elongated closed tube connected to said chamber and extending away from said turbine nozzle vanes; a transducer exposed to pressure oscillations in said tube for providing a signal output as a function of the pressure oscillations in said chamber.

Claim 7

A gas turbine engine comprising: a compressor for pressurizing a source of air; a combustor for receiving pressurized air from said compressor and for generating a hot gas stream; a turbine assembly downstream of said combustor and having a turbine inlet nozzle through which said hot gas stream passes, said turbine nozzle comprising a plurality of radially extending hollow vanes; means for providing a flow path for pressurized cooling air from said compressor through the interior of said vanes; a fluidic oscillator connected to the hot gas stream passing through said turbine nozzle and being positioned in the interior of said vanes, whereby the exterior of said fluidic oscillator is maintained at the temperature of said cooling air; and means exterior of said turbine nozzle assembly for providing a signal output proportional to the pressure oscillations in said fluidic oscillator.

Claim 8

A gas turbine engine comprising: a compressor for pressurizing a source of air; a combustor for receiving pressurized air from said compressor and for generating a hot gas stream; a turbine assembly downstream of said combustor and having a turbine inlet nozzle through which said hot gas stream passes, said turbine nozzle comprising a plurality of radially extending hollow vanes; means for providing a flow path for pressurized cooling air from said compressor through the interior of said vanes; a fluidic oscillator connected to the hot gas stream passing through said turbine nozzle and being positioned in the interior of said vanes, whereby the exterior of said fluidic oscillator is maintained at the temperature of said cooling air; and means exterior of said turbine nozzle assembly for providing a signal output proportional to the pressure oscillations in said fluidic oscillator.

Claim 9

A gas turbine engine as in claim 6 wherein said fluidic oscillator comprises: a chamber positioned in the interior of one of said turbine nozzle vanes and having an inlet extending to the leading edge thereof and an outlet extending to a throat portion in said turbine nozzle assembly; said means for providing a signal output comprises a closed tube connected to said oscillating chamber and extending away from said turbine nozzle assembly and a transducer connected to said tube for providing a signal output proportional to the oscillations in said tube.