Air-driven particle pulverizer for gas turbine engine cooling fluid system
A cooling fluid system for a gas turbine engine includes a structure that provides a fluid passageway. The structure has a wall with an aperture that is in fluid communication with the fluid passageway. The aperture is configured to provide a fluid in a flow direction. Fingers are arranged in the fluid passageway facing into flow direction. The fluid passageway includes a cooling cavity immediately downstream from the fingers and it is configured to receive fluid having passed over or through the fingers.
1. A cooling fluid system for a gas turbine engine comprising:
a structure providing a fluid passageway, the structure having a wall with an aperture in fluid communication with the fluid passageway, the aperture being configured to provide a fluid in a flow direction; and
fingers arranged in the fluid passageway facing into the flow direction wherein each of the fingers comprises a base and a terminal end, each finger extending from the base toward the aperture to the terminal end, each terminal end exposed to fluid flowing from the aperture, the aperture configured to impinge the fluid substantially directly onto each terminal end for pulverizing particles in the fluid, the fluid passageway including a cooling cavity immediately downstream from the fingers and configured to receive fluid having passed over or through the fingers,
wherein the fingers are spaced along the flow direction relative to one another, and
wherein an acute angle is formed between adjacent fingers.
2. The cooling fluid system according to claim 1 , comprising a cooling fluid source in fluid communication with the structure upstream from the aperture.
3. The cooling fluid system according to claim 2 , wherein the cooling fluid source is a compressor section, and the structure is an engine static structure arranged in a turbine section.
4. The cooling fluid system according to claim 3 , wherein the engine static structure is a vane support.
5. The cooling fluid system according to claim 1 , wherein the fingers are canted toward the aperture.
6. The cooling fluid system according to claim 5 , wherein the aperture is oriented toward the fingers.
7. The cooling fluid system according to claim 1 , wherein the fingers are each tapered to an apex.
8. The cooling fluid system according to claim 1 , wherein the fingers include a coating providing a hardness greater than a finger substrate.
9. The cooling fluid system according to claim 1 , wherein a recess is provided between adjacent fingers.
10. The cooling fluid system according to claim 1 , wherein the fingers increase in length as a distance from the aperture increases.
11. The cooling fluid system according to claim 1 , wherein a blade outer air seal is arranged in the cooling cavity.
12. The cooling fluid system according to claim 1 , wherein the fingers are formed from a nickel alloy.
13. A cooling fluid system for a gas turbine engine comprising:
a structure providing a fluid passageway, the structure having a wall with an aperture in fluid communication with the fluid passageway, the aperture being configured to provide a fluid in a flow direction;
a cooling fluid source in fluid communication with the structure upstream from the aperture, wherein the cooling fluid source is a compressor section, and the structure is a vane support of an engine static structure arranged in a turbine section; and
fingers arranged in the fluid passageway facing into the flow direction wherein each of the fingers comprises a base and a terminal end, each finger extending from the base toward the aperture to the terminal end, each terminal end being directed at the aperture, the fluid passageway including a cooling cavity downstream from the fingers and configured to receive unobstructed fluid from the fingers, wherein the engine static structure includes a blade outer air seal arranged in the cooling cavity and downstream from the fingers.