Turbine engine with shockwave attenuation

Patent metadata

Field	Value
Publication number	US-11519333-B2
Application number	US-202017016670-A
Country	US
Kind code	B2
Filing date	Sep 10, 2020
Priority date	Sep 10, 2020
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

Aspects of the disclosure generally relate to a turbine engine and method of operating a turbine engine having an engine core including a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core. The method includes generating a shockwave in the working airflow that propagates in the flow direction, and at least partially attenuating the shockwave.

First claim

What is claimed is:

1. A method of operating a turbine engine having an engine core comprising a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core, the method comprising:
generating a shockwave in the working airflow that propagates onto an outer surface of at least one component within the turbine engine having at least one attenuation structure; and
flowing cooling air from an interior of the at least one component through the at least one attenuation structure into the working airflow in a direction at least partially opposite the flow direction to at least partially attenuate the shockwave.

2. The method of claim 1 wherein the at least one component comprises at least one of an airfoil, an inner band, or an outer band.

3. The method of claim 1 , further comprising directing a reflected portion of the shockwave over a second attenuation structure on a second component to attenuate the reflected portion.

4. The method of claim 1 wherein the at least one component comprises two circumferentially-spaced airfoils, and wherein the directing further comprises directing the shockwave between the two circumferentially-spaced airfoils.

5. The method of claim 1 wherein the shockwave comprises a pressure wave within a subsonic flow.

6. A turbine engine, comprising:
an engine core comprising a compressor, combustor, and turbine in axial flow arrangement;
a flow path extending through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core;
a rotatable set of airfoils in one of the compressor or turbine, whereby rotation of the set of airfoils forms the working airflow having a shockwave;
at least one component in the flow path comprising an outer surface bounding an interior, with the shockwave flowing onto the outer surface; and
at least one attenuation structure on the outer surface comprising a set of cooling holes having corresponding outlets oriented at least partially in a direction opposite the flow direction to at least partially attenuate the shockwave flowing onto the outer surface.

7. The turbine engine of claim 6 , further comprising a second component comprising a second attenuation structure configured to attenuate a reflected shockwave flowing thereon.

8. The turbine engine of claim 6 wherein the at least one component comprises an airfoil with the outer surface defining a pressure side and a suction side and extending between a leading edge and a trailing edge.

Assignees

• Gen Electric

Inventors

• Johnson Christopher Ryan
• Vitt Paul Hadley
• Schroeder Eric Joseph
• Fernandez-Soto Carlos Gilberto

Classifications

• F02C7/00

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title

• F05D2250/60

  Structure; Surface texture · CPC title

• F02C7/24 Primary

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F02C3/04 Primary

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title