Gas turbine engine vane outer diameter platform integrated with blade outer air seal

Patent metadata

Field	Value
Publication number	US-12435640-B2
Application number	US-202318500671-A
Country	US
Kind code	B2
Filing date	Nov 2, 2023
Priority date	Nov 2, 2023
Publication date	Oct 7, 2025
Grant date	Oct 7, 2025

Abstract

A combined gas turbine engine vane and blade outer air seal assembly includes a vane having an airfoil extending from the leading edge to a trailing edge, and has an outer platform. The outer platform has a cooling channel that extends into the airfoil to receive cooling air. The outer platform extends to an integral blade outer air seal to be positioned radially outwardly of a turbine blade in a gas turbine engine. At least a portion of the vane and the blade outer air seal are formed of ceramic matrix composite materials. A gas turbine engine is also disclosed.

First claim

What is claimed is:

1. A combined gas turbine engine vane and blade outer air seal assembly comprising:
a vane having an airfoil extending from a leading edge to a trailing edge, and having an outer platform, the outer platform having a cooling channel that extends into the airfoil to receive cooling air;
the outer platform extending to an integral blade outer air seal to be positioned radially outwardly of a turbine blade in a gas turbine engine;
at least a portion of said vane and said blade outer air seal formed of ceramic matrix composite materials;
wherein there are cooling air passages within said outer platform and said blade outer air seal and connected into the cooling channel such that the cooling air can be communicated from the cooling channel into said blade outer air seal; and
wherein the cooling air passages extend to a radially outwardly extending portion and then into outlets extending in an axially aft direction.

2. The assembly as set forth in claim 1 , wherein there is an enclosed portion of the blade outer air seal radially outward of the outlets.

3. A gas turbine engine comprising:
a compressor section, a combustor section, and a turbine section, the turbine section including a combined vane and blade outer air seal assembly having a vane having an airfoil extending from a leading edge to a trailing edge, and having an outer platform, the outer platform having a cooling channel that extends into the airfoil to receive cooling air;
the outer platform extending to an integral blade outer air seal positioned radially outwardly of a turbine blade in the turbine section;
at least a portion of said vane and said blade outer air seal formed of ceramic matrix composite materials;

wherein there are cooling air passages within said outer platform and said blade outer air seal and connected into the cooling channel such that the cooling air can be communicated from the cooling channel into said blade outer air seal; and
wherein the cooling air passages extend to a radially outwardly extending portion and then into outlets extending in an axially aft direction.

4. The gas turbine engine as set forth in claim 3 , wherein there is an enclosed portion of the blade outer air seal radially outward of the outlets.

Assignees

• Rtx Corp

Inventors

• Roach James T
• Banhos Jonas
• Kim Russell

Classifications

• F01D5/187

  Convection cooling · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F05D2300/6034

  Orientation of fibres, weaving, ply angle · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2240/81

  Cooled platforms · CPC title