Microcircuit cooling for gas turbine engine combustor

• US 9,057,523 B2
• Filed: 07/29/2011
• Issued: 06/16/2015
• Est. Priority Date: 07/29/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Cunha, Frank J., Snyder, Timothy S.
• Primary Examiner(s): NGUYEN, ANDREW H
• Application Number:
  US13/193,696
• Publication Number:
  US 20130025288A1
• Time in Patent Office: 1,418 Days
• Field of Search: 60752-760
• US Class Current: 1/1
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F23R 2900/00018 Manufacturing combustion chamber liners or subparts
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03043 Convection cooled combustion chamber walls with means for guiding the cooling air flow
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/04 Air inlet arrangements
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: F23R 3/12 inducing a vortex
• CPC Class Codes: F23R 3/14 by using swirl vanes

Abstract

A combustor component of a gas turbine engine including a heat shield panel. The heat shield panel a defines microcircuit flow path within a thickness of said heat shield panel.

Claims

1. A combustor component of a gas turbine engine comprising:

a heat shield panel defining a microcircuit flow path within a thickness of said heat shield panel and provided with an inlet and an outlet; and

a flow swirler received in a dilution hole defined by said heat shield panel, said flow swirler downstream of and in communication with a microcircuit flow from said microcircuit flow path and with a diffusion flow from said dilution hole, wherein said diffusion flow is communicated from an annular passageway between a combustor case and said heat shield and wherein said flow swirler is configured to eject flow from said outlet in a tangential direction with respect to an axial flow path and to a combustion chamber defined by the heat shield panel.

2. The combustor component as recited in claim 1, wherein said heat shield panel is a forward heat shield panel.

3. The combustor component as recited in claim 1, further comprising a support shell, said heat shield panel mounted to said support shell, and said dilution hole defined along a common axis by said heat shield panel and said support shell.

4. The combustor component as recited in claim 3, wherein said support shell is mounted to said combustor case.

5. The combustor component as recited in claim 1, wherein said heat shield panel includes a multiple of internal features positioned in said microcircuit flow path.

6. The combustor component as recited in claim 5, wherein said multiple of internal features repeat tangentially and axially throughout said heat shield panel.

7. The combustor component as recited in claim 5, wherein said microcircuit flowpath includes said inlet and said outlet upstream of the flow swirler.

8. The combustor component as recited in claim 7, further comprising a wall depression located on a hot side of said heat shield panel downstream of said outlet and spaced from said microcircuit flowpath, said wall depression configured to provide firm wall attachment of flow communicated from said outlet onto said hot side.

9. The combustor component as recited in claim 5, wherein said multiple of internal features include a pair of islands arranged in said microcircuit flow path configured to meter flow through said microcircuit flow path.