Seal assembly for a static structure of a gas turbine engine
AssigneeUnited Technologies Corporation
InventorGrace E. Szymanski
Life of this patent
Estimating the term…
Abstract
A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.
Claims20
A gas turbine engine, comprising:
- a compressor section;
- a combustor section in fluid communication with said compressor section;
- a turbine section in fluid communication with said combustor section;
- and
- a static structure disposed within a core flow path in one of said compressor section and said turbine section and having:
- an outer platform;
- an inner platform;
- an airfoil that extends between said outer platform and said inner platform;
- a service tube disposed at least partially through said airfoil;
- and
- a seal assembly that seals between said service tube and one of said outer platform and said inner platform.
The gas turbine engine as recited in 2, wherein said mid-turbine frame is arranged between a high pressure turbine and a low pressure turbine of said turbine section.
A gas turbine engine, comprising:
- a compressor section;
- a combustor section in fluid communication with said compressor section;
- a turbine section in fluid communication with said combustor section;
- and
- a static structure disposed within a core flow path in one of said compressor section and said turbine section and having:
- an outer platform;
- an inner platform;
- an airfoil that extends between said outer platform and said inner platform;
- a service tube disposed at least partially through said airfoil;
- and
- a seal assembly that seals between said service tube and one of said outer platform and said inner platform, said seal assembly including a locking plate received within a groove of said service tube.
A gas turbine engine, comprising:
- a compressor section;
- a combustor section in fluid communication with said compressor section;
- a turbine section in fluid communication with said combustor section;
- and
- a static structure disposed in one of said compressor section and said turbine section and having:
- an outer platform;
- an inner platform;
- an airfoil that extends between said outer platform and said inner platform;
- a service tube extending within said airfoil and including a tube end fitting that includes a first groove and a second groove;
- a seal positioned in said first groove for sealing between said service tube and a neighboring component;
- and
- a locking plate positioned in said second groove for sealing between said service tube and one of said outer platform and said inner platform.
Dependencies are inferred from the claim text.