Turbine engine with anti-ice valve assembly, bleed air valve, and method of operating
An anti-ice valve, a turbine engine including an anti-ice valve assembly and a method of operating an anti-ice valve where an anti-ice valve has a housing and a valve element configured to control a flow of hot bleed air through the housing, and a muscle air passage extending through the housing, a cooling air passage extending through the housing, and a heat exchanger located within the housing and having heat transfer surfaces in thermal communication with the muscle air passage and the cooling air passage.
1. A bleed air valve assembly, comprising:
a bleed air valve having a housing and a valve element configured to control a flow of hot bleed air, at a first temperature, through the housing, wherein the housing includes a servo housing forming a portion of a pneumatic servo controller, and a separate valve element housing;
a muscle air passage extending through the servo housing;
a cooling air passage extending through the servo housing, wherein a cooling air is at a second temperature that is less than the first temperature; and
a heat exchanger located within the servo housing and having heat transfer surfaces in thermal communication with the muscle air passage and the cooling air passage, wherein heat is transferred from muscle air within the muscle air passage to cooling air in the cooling air passage by the heat transfer surfaces to effect a cooling of the muscle air, and define a third temperature muscle air stream, wherein the third temperature is less than the first temperature and greater than the second temperature, wherein the servo housing defines a cavity that houses the heat exchanger, and wherein the cavity is formed at least by a first wall of the servo housing extending from a second wall of the servo housing to a third wall of the servo housing, the second and third walls being horizontal walls.
2. The bleed air valve assembly of claim 1 wherein the muscle air passage includes multiple passages forming a muscle air circuit and the cooling air passage includes multiple passages forming a cooling air circuit.
3. The bleed air valve assembly of claim 1 wherein the heat exchanger is integrally formed with the servo housing.
4. The bleed air valve assembly of claim 1 wherein the servo housing and valve element housing are spaced apart from each other.
5. The bleed air valve assembly of claim 1 , further comprising a muscle air outlet fluidly coupling the servo housing to the valve element housing such that muscle bleed air is provided to the valve element housing through the muscle air outlet.
6. The bleed air valve assembly of claim 1 wherein the heat exchanger is a multi-pass heat exchanger.
7. The bleed air valve assembly of claim 1 wherein the heat exchanger is a compact heat exchanger having dense finned surfaces.
8. A gas turbine engine comprising:
an engine core having an inner housing containing a fan assembly, a compressor section, a combustion section, and a turbine section;
a nacelle anti-icing system configured to tap compressed air from the engine core to a portion of a nacelle to define a flow of hot bleed air, wherein the hot bleed air is a first temperature; and
an anti-ice valve assembly comprising:
a valve element housing defining a flow path;
a valve element disposed in the flow path configured to control the flow of hot bleed air to the nacelle; and
a servo controller comprising:
a servo housing forming a portion of the servo controller;
a muscle air passage extending through the servo housing and fluidly coupled to the flow of hot bleed air;
a cooling air passage extending through the servo housing, wherein a cooling air is at a second temperature that is less than the first temperature; and
a heat exchanger located within the servo housing, and having heat transfer surfaces in thermal communication with the muscle air passage and the cooling air passage and wherein heat is transferred from muscle air within the muscle air passage to cooling air in the cooling air passage by the heat transfer surfaces to effect a cooling of the muscle air and define a third temperature muscle air stream, wherein the third temperature is less than the first temperature and greater than the second temperature, wherein the servo housing defines a cavity that houses the heat exchanger, and wherein the cavity is formed at least by a first wall of the servo housing extending from a second wall of the servo housing to a third wall of the servo housing, the second and third walls being horizontal walls.
9. The gas turbine engine of claim 8 wherein the muscle air passage includes multiple passages forming a muscle air circuit and the cooling air passage includes multiple passages forming a cooling air circuit.
10. The gas turbine engine of claim 8 wherein the heat exchanger is integrally formed with the servo housing.
11. The gas turbine engine of claim 8 wherein the servo housing and valve housing are spaced apart from each other.
12. The gas turbine engine of claim 8 wherein the heat exchanger is a multi-pass heat exchanger.
13. The gas turbine engine of claim 8 wherein the heat exchanger is a compact heat exchanger having dense finned surfaces.
14. The gas turbine engine of claim 8 wherein the cooling air passage is fluidly coupled to the fan assembly of the engine core.
15. The gas turbine engine of claim 8 wherein the compressed air is tapped from the turbine section of the engine core.
16. The gas turbine engine of claim 8 wherein the servo controller controls the valve element and regulates the pressure of the bleed air through the flow path.
17. A method of operating an anti-ice valve, the method comprising:
supplying a flow of hot compressed air to the anti-ice valve;
diverting a portion of the flow of hot compressed air to form a flow of muscle air; and
passing the flow of muscle air through a compact heat exchanger having dense finned surfaces, while supplying cooling air to a portion of the compact heat exchanger that is fluidly separate from the flow of muscle air to extract heat from the flow of muscle air to define a flow of cooled muscle air;
wherein the compact heat exchanger is located within a servo housing of the anti-ice valve, the servo housing forming a portion of a pneumatic servo controller, wherein the servo housing defines a cavity that houses the heat exchanger, the dense finned surfaces being inside the cavity, and wherein the cavity is formed at least by a first wall of the servo housing extending from a second wall of the servo housing to a third wall of the servo housing, the second and third walls being horizontal walls.
18. The method of claim 17 , further comprising utilizing the flow of cooled muscle air to operate a portion of the anti-ice valve.
19. The method of claim 17 wherein diverting the portion of the flow of hot compressed air includes diverting the portion upstream of the anti-ice valve.