Thermally loaded, cooled component

• US 9,022,726 B2
• Filed: 06/24/2011
• Issued: 05/05/2015
• Est. Priority Date: 06/25/2010
• Status: Active Grant

• Current Assignee: Ansaldo Energia Switzerland AG (Ansaldo Energia SPA)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Szwedowicz, Jaroslaw Leszek, Irmisch, Stefan
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): LEGENDRE, CHRISTOPHER RYAN
• Application Number:
  US13/167,819
• Publication Number:
  US 20110318191A1
• Time in Patent Office: 1,411 Days
• Field of Search: 165/109.1, 165/168, 165/908, 415/115, 416/97.R
• US Class Current: 415/115
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/221 Improvement of heat transfer
• CPC Class Codes: F05D 2260/963 by Helmholtz resonators
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A thermally loaded, cooled component thermally coupled to a cooling system configured to receive a gaseous cooling introduced in a forced manner from outside that flows through the cooling system so as to absorb and transport heat away from the component as a result of thermal contact with the component. The component includes at least one Helmholtz resonator configured to improve thermal contact between the cooling medium and the component.

Claims

1. A turbine blade configured to be thermally loaded and coupled to a cooling system configured to receive a gaseous cooling medium introduced in a forced manner from outside the turbine blade that flows through the cooling system so as to absorb and transport heat away from the turbine blade as a result of thermal contact with the turbine blade, the turbine blade comprising:

at least one Helmholtz resonator configured to improve thermal contact between the cooling medium and the turbine blade, the at least one Helmholtz resonator including an enclosure having a constricted entrance;

wherein the turbine blade includes a cooled blade airfoil including an interior through which the gaseous cooling medium flows, and wherein the at least one Helmholtz resonator is disposed in the interior of the blade airfoil; and

wherein the blade airfoil includes a plurality of cooling passages extending in parallel in a radial direction, and wherein the Helmholtz resonators are integrated into the cooling passages.

2. The turbine blade recited in claim 1, wherein the blade airfoil comprises:

a leading edge and a trailing edge, and wherein the at least one Helmholtz resonator is disposed in a region of the leading edge.

3. The turbine blade recited in claim 1, wherein the at least one Helmholtz resonator is in fluidic communication with the cooling system and is configured to be excited into vibrations by the flow of the cooling medium.

4. The turbine blade recited in claim 3, wherein the at least one Helmholtz resonator is integrated into the cooling system.

5. The turbine blade recited in claim 1, wherein the at least one Helmholtz resonator includes a plurality of Helmholtz resonators disposed next to each other, each of the plurality of Helmholtz resonators being fluidicaly interconnected by a connecting passage and configured to form an acoustic heat pump.

6. The turbine blade recited in claim 1, wherein the at least one Helmholtz resonator is disposed in a region within the turbine blade configured for particularly high thermal loading.

7. The turbine blade recited in claim 1, wherein the turbine blade is part of a heat engine.

8. The turbine blade recited in claim 7, wherein the heat engine is one of a steam or gas turbine.