CN-115387912-B - Gas turbine engine with fluid circuit and ejector

Abstract

A gas turbine engine is provided having a static structure including a flow path wall. The fluid circuit extends through the flow path wall and includes a first inlet opening in fluid communication with the first cavity to receive a first fluid flow through the fluid circuit. The static structure includes an eductor positioned at the fluid circuit, wherein the eductor includes a second inlet opening in fluid communication with the second chamber to receive a second fluid flow through the eductor and into the fluid circuit.

Inventors

• Thomas Edward bodowski
• Miroslo Sobanik
• Machee Stawansky
• Ashes Sharma
• Piot YeGe kulinski

Assignees

• 通用电气波兰有限公司
• 通用电气德国控股有限公司

Dates

Publication Date

20260505

Application Date

20211027

Priority Date

20210524

Claims (17)

1. 1. A gas turbine engine, the engine comprising: A vane assembly comprising a flow path wall, wherein a fluid circuit extends through the flow path wall, and wherein the fluid circuit defines a first inlet opening in fluid communication with a first cavity to receive a first fluid flow through the fluid circuit, and wherein the vane assembly comprises an ejector positioned at the fluid circuit, wherein the ejector defines a second inlet opening in fluid communication with a second cavity to receive a second fluid flow through the ejector and into the fluid circuit, the second cavity being fluidly isolated from the first cavity, the second fluid flow having a higher pressure and temperature than the first fluid flow, Wherein the ejector comprises a nozzle positioned downstream of the second inlet opening with respect to the second fluid flow towards the fluid circuit, and Wherein the nozzle is configured to push the first fluid flow through the fluid circuit by injecting the second fluid flow from the second inlet opening through the nozzle into the fluid circuit.
2. 2. The gas turbine engine of claim 1, wherein the second inlet opening is positioned downstream of the first inlet opening along the fluid circuit.
3. 3. The gas turbine engine of claim 1, wherein the nozzle includes a converging cross-sectional area from the second inlet opening toward an outlet opening of the fluid circuit relative to the second fluid flow.
4. 4. The gas turbine engine of claim 1, wherein the fluid circuit forms a converging-diverging nozzle positioned at the fluid circuit downstream of the nozzle.
5. 5. The gas turbine engine of claim 1, wherein the fluid circuit forms a twisted flow path, a grid structure, or a lattice structure through the vane assembly.
6. 6. The gas turbine engine of claim 5, wherein the fluid circuit includes a straight portion extending in a longitudinal direction, a radial direction, or a circumferential direction, and wherein the fluid circuit includes a curved portion configured to rotate the first fluid flow.
7. 7. The gas turbine engine of claim 1, wherein the vane assembly includes an airfoil, wherein the flow path wall is an airfoil flow path surface, and wherein the airfoil includes a double wall structure through which the fluid circuit extends.
8. 8. The gas turbine engine of claim 7, wherein the double-wall structure includes the airfoil flow path surface formed at a pressure side and a suction side of the airfoil, and wherein the double-wall structure includes an inner airfoil surface inboard of the airfoil flow path surface, and wherein the fluid circuit extends between the airfoil flow path surface and the inner airfoil surface.
9. 9. The gas turbine engine of claim 8, wherein the airfoil forms an airfoil cavity inboard of the inner airfoil surface, wherein the second cavity is the airfoil cavity, and wherein the second inlet opening is in fluid communication with the airfoil cavity to receive the second fluid flow therefrom into the fluid circuit.
10. 10. The gas turbine engine of claim 7, wherein the airfoil includes a leading edge and a trailing edge, and wherein the fluid circuit extends from proximate the leading edge to proximate the trailing edge.
11. 11. The gas turbine engine of claim 10, wherein the first inlet opening is proximate the leading edge relative to the trailing edge.
12. 12. The gas turbine engine of claim 1, wherein the engine comprises: a compressor section, a combustion section, and a turbine section in serial flow order, wherein the vane assembly is positioned at one or more of the compressor section, the combustion section, or the turbine section.
13. 13. The gas turbine engine of claim 1, wherein the vane assembly includes an outer band, and wherein the fluid circuit extends along the outer band.
14. 14. The gas turbine engine of claim 13, wherein the outer band at least partially forms a gas flow path of the engine through which combustion gases flow.
15. 15. The gas turbine engine of claim 1, wherein the vane assembly includes an inner band, and wherein the fluid circuit extends through the inner band.
16. 16. A static structure for a gas turbine engine, the static structure comprising: a flow path wall, wherein a fluid circuit extends through the flow path wall, and wherein the fluid circuit includes a first inlet opening in fluid communication with a first cavity to receive a first fluid flow through the fluid circuit, and wherein the static structure includes an ejector positioned at the fluid circuit, wherein the ejector includes a second inlet opening in fluid communication with a second cavity to receive a second fluid flow through the ejector and into the fluid circuit, the second cavity being fluidly isolated from the first cavity, the second fluid flow having a higher pressure and temperature than the first fluid flow, Wherein the injector comprises a nozzle configured to push the first fluid flow through the fluid circuit by injecting the second fluid flow from the second inlet opening through the nozzle into the fluid circuit, and Wherein the fluid circuit further comprises an outlet opening downstream of the ejector, Wherein the outlet opening is in fluid communication with an outlet cavity, wherein the outlet cavity is fluidly isolated from a gas flow path through the gas turbine engine.
17. 17. The static structure of claim 16, wherein the static structure comprises a double wall structure through which the fluid circuit extends.

Description

Gas turbine engine with fluid circuit and ejector Government sponsored research Leading to the project of the present application having been sponsored by the European Union clean sky No.2 research and innovation project, sponsored protocol number CS2-ENG-GAM-2014-2015-01. Technical Field The present subject matter relates generally to cooling structures for gas turbine engines. Background The gas turbine engine generates high temperature gas that is in thermal contact with the component through a gas flow path. High temperature gases wear and degrade gas turbine engine components, and sometimes the high temperature gases may exceed the melting point or other critical temperature of certain components at the gas flow path. Gas turbine engines typically include cooling circuits and structures to reduce component temperatures, thereby reducing wear and degradation of the high temperature gases. Such cooling circuits typically remove relatively cool air from the compressor and direct the air to other components, such as the combustor and turbine section components, to provide the desired cooling. The input energy that would otherwise flow to the combustion process is removed and bypassed using compressed air, particularly high pressure, high energy compressed air from the compressor section, and the compressed air is used for cooling purposes. Thus, such methods and structures for cooling compromise the thermodynamic performance and efficiency of the engine in terms of structural durability and component life. Accordingly, there is a need for improved cooling structures for gas turbine engines. In addition, there is a need for improved structures for cooling to reduce the losses associated with the use of relatively high pressure air. Disclosure of Invention Aspects and advantages of the disclosure will be set forth in part in the description which follows, or may be obvious from the description, or may be learned by practice of the disclosure. One aspect of the invention relates to a gas turbine engine having a bucket assembly including a flow path wall. A fluid circuit extends through the flow path wall. The fluid circuit defines a first inlet opening in fluid communication with the first cavity to receive a first fluid flow through the fluid circuit. The vane assembly includes an ejector positioned at the fluid circuit. The eductor defines a second inlet opening in fluid communication with the second chamber to receive a second fluid flow through the eductor and into the fluid circuit. Another aspect of the present disclosure relates to a static structure for a gas turbine engine. The static structure includes a flow path wall having a fluid circuit extending through the flow path wall. The fluid circuit includes a first inlet opening in fluid communication with the first cavity to receive a first fluid flow through the fluid circuit. The static structure includes an ejector positioned at the fluid circuit. The eductor includes a second inlet opening in fluid communication with the second chamber to receive a second fluid flow through the eductor and into the fluid circuit. These and other features, aspects, and advantages of the present disclosure will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate various aspects of the present disclosure and together with the description, serve to explain the principles of the disclosure. Drawings A full and enabling disclosure, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which: FIG. 1 is a schematic embodiment of an exemplary engine according to aspects of the present disclosure; FIG. 2 is a schematic embodiment of an exemplary combustion section for an engine according to aspects of the present disclosure; FIG. 3 is a perspective view of a portion of a static structure having a fluid circuit according to aspects of the present disclosure; FIG. 4 is a perspective view of an embodiment of a portion of a static structure having a fluid circuit in accordance with aspects of the present disclosure, and FIG. 5 is a perspective view of an embodiment of a portion of a static structure having a fluid circuit in accordance with aspects of the present disclosure, and FIG. 6 is a cross-sectional view of an embodiment of an ejector at a fluid circuit according to aspects of the present disclosure; FIG. 7 is a cross-sectional view of an embodiment of an ejector at a fluid circuit according to aspects of the present disclosure; FIG. 8 is a cross-sectional view of an embodiment of a static structure having a fluid circuit according to aspects of the present disclosure; FIG. 9 is a cross-sectional view of an embodiment of a static structure having a fluid circuit according to aspects of the present disclosure; FIG. 10