Bore-cooled film dispensing pedestals

Patent metadata

Field	Value
Publication number	US-10563583-B2
Application number	US-201415022990-A
Country	US
Kind code	B2
Filing date	Oct 16, 2014
Priority date	Oct 30, 2013
Publication date	Feb 18, 2020
Grant date	Feb 18, 2020

Abstract

A cooling circuit for a gas turbine engine comprises a first wall having a first surface facing a first cavity and a second surface facing away from the first cavity. A second wall is spaced outwardly of the second surface of the first wall to provide at least one second cavity. Cooling fluid is configured to flow from the first cavity and exit to an external surface of the second wall via at least one hole to provide cooling to the external surface. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

First claim

The invention claimed is:

1. A cooling circuit for a gas turbine engine comprising:
a first wall having a first surface facing a first cavity and a second surface facing away from the first cavity;
a second wall spaced from the first wall to provide at least one second cavity formed between the first and second walls, wherein the second wall includes an inner surface facing the second cavity and an external surface facing opposite the inner surface, and wherein cooling fluid is configured to flow from the first cavity and exit to the external surface of the second wall via at least one hole to provide cooling to the external surface;
at least one pedestal having a first end connected to the second surface of the first wall and a second end connected to the inner surface of the second wall such that the at least one pedestal extends across the at least one second cavity, the at least one pedestal including at least one internal cooling channel that fluidly connects the first cavity to the at least one hole at the external surface; and
wherein the at least one internal cooling channel comprises a plurality of internal cooling channels, wherein the at least one hole comprises a plurality of holes, and wherein the at least one pedestal comprises a plurality of pedestals each including at least one internal cooling channel of the plurality of cooling channels that exits to the external surface via at least one hole of the plurality of holes, and wherein the first end of each pedestal is connected to the second surface of the first wall and the second end of each pedestal is connected to the inner surface of the second wall, and wherein cooling fluid has a first flow path that flows through the at least one second cavity and around the pedestals and then exits directly to the external surface to provide a first flow path outlet and a second flow path that flows through the internal cooling channels of the pedestals from the first cavity to the plurality of holes at the external surface to provide a second flow path outlet.

2. The cooling circuit according to claim 1 wherein the first flow path comprises at least one of an axial or radial flow and wherein the second flow path is orientated at an oblique angle relative to the first flow path.

3. The cooling circuit according to claim 1 wherein the second wall is configured to provide an airfoil section, and wherein the first flow path outlet comprises a plurality of slots adjacent a trailing edge of the airfoil and wherein the plurality of holes comprises a plurality of film cooling holes that are spaced from the plurality of slots.

4. The cooling circuit according to claim 1 wherein the plurality of holes are formed in a pressure side of an airfoil.

5. A cooling circuit for a gas turbine engine comprising:
a first wall having a first surface facing a first cavity and a second surface facing away from the first cavity;
a second wall spaced from the first wall to provide at least one second cavity formed between the first and second walls, wherein the second wall includes an inner surface facing the second cavity and an external surface facing opposite the inner surface, and wherein cooling fluid is configured to flow from the first cavity and exit to the external surface of the second wall via at least one hole to provide cooling to the external surface;
at least one pedestal having a first end connected to the second surface of the first wall and a second end connected to the inner surface of the second wall such that the at least one pedestal extends across the at least one second cavity, the at least one pedestal including at least one internal cooling channel that fluidly connects the first cavity to the at least one hole at the external surface; and
wherein the first wall comprises an internal wall and the first cavity comprises a center cavity, and wherein the second wall comprises an outer wall and the second cavity comprises an outer wall cavity with the at least one pedestal being located within the outer wall cavity, and wherein the at least one hole comprises at least one film cooling hole, and wherein the cooling fluid has at least a first flow path and a second flow path that is separate from the first flow path, wherein the first flow path flows through the outer wall cavity, around the at least one pedestal, and exits the outer wall cavity directly to the external surface via a first flow path outlet, and wherein the second flow path flows from the center cavity, through the at least one internal cooling channel, and directly exits to the external surface via the at least one film cooling hole which comprises a second flow path outlet.

6. The cooling circuit according to claim 5 wherein the outer wall with the at least one film cooling hole comprises a hot exterior surface of an airfoil.

7. The cooling circuit according to claim 6 wherein the at least one pedestal comprises a plurality of pedestals each having the first end associated with the second surface of the internal wall and the second end associated with the inner surface of the outer wall, and wherein the at least one pedestal of the plurality of pedestals that includes the at least one internal cooling channel has the first end open to the center cavity and the second end open to the external surface via the at least one film cooling hole.

8. A gas turbine engine comprising:
a compressor section;
a combustor section downstream of the compressor section;
a turbine section downstream of the combustor section, and wherein at least one of the combustor section and the turbine section include a component having a first wall with a first surface facing a first cavity and a second surface facing away from the first cavity, and a second wall spaced from the first wall to provide at least one second cavity formed between the first and second walls, wherein the second wall includes an inner surface facing the second cavity and an external surface facing opposite the inner surface, and wherein cooling air is configured to flow from the first cavity and exit to the external surface of the second wall via at least one hole to provide cooling to the external surface, and including at least one pedestal having a first end connected to the second surface of the first wall and a second end connected to the inner surface of the second wall such that the at least one pedestal extends across the at least one second cavity, the at least one pedestal including at least one internal cooling channel that fluidly connects the first cavity to the at least one hole at the external surface; and
wherein the at least one hole comprises a plurality of holes, and wherein the at least one pedestal comprises a plurality of pedestals wherein the first end of each pedestal is connected to the second surface of the first wall and the second end of each pedestal is connected to the inner surface of the second wall and with at least one pedestal of the plurality of pedestals having the at least one internal cooling channel exiting to the external surface via the at least one hole such that cooling fluid has a first flow path that flows through the at least one second cavity and around the plurality of pedestals, and exits the second cavity directly to the external surface via a first flow path outlet, and including a second flow path that flows through the internal cooling channels of the plurality of pedestals from the first cavity and directly exits to the external surface via the plurality of holes which comprise a second flow path outlet.

9. The gas turbine engine according to claim 8 wherein the component comprises a combustor panel, blade outer air seal, airfoil platform, or turbine exhaust duct.

10. The gas turbine engine according t

Assignees

• United Technologies Corp

Inventors

• Slavens Thomas N
• Snyder Brooks E

Classifications

• F05D2260/204

  by the use of microcircuits · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F05D2240/305

  related to the pressure side of a rotor blade · CPC title