Sealing system for sealing against a non-cylindrical surface
AssigneeGeneral Electric Company
InventorsDonald Michael Corsmeier, Donald Scott Yeager
Life of this patent
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Abstract
The present disclosure is directed to a sealing system for a turbine engine including an engine component, the engine component defining an oblique sealing surface defining an annular shape. The oblique sealing surface defines an oblique angle with a centerline of the engine component. The sealing system includes a seal housing and a seal ring. The seal housing is annular and includes a groove that is defined by a first sidewall, a second sidewall, and an end wall connecting the first sidewall and the second sidewall. The seal ring is positioned at least partially within the groove in the seal housing. The seal ring defines a seal contact surface for forming a seal with the oblique sealing surface of the engine component.
Claims14
A sealing system for a turbine engine comprising a combustor, the combustor comprising an inner liner having an inside surface, the inside surface defining an oblique sealing surface defining an annular shape about an axial centerline of the engine, the oblique sealing surface defining an oblique angle with the axial centerline of the turbine engine, wherein the oblique sealing surface also defines an oblique angle with the centerline of the combustor, the sealing system comprising:
- a seal housing disposed radially inward of the inner liner, wherein the seal housing is annular about the axial centerline of the turbine engine and includes a groove that is defined by a first sidewall, a second sidewall, and an end wall connecting the first sidewall and the second sidewall, wherein the end wall opposes the oblique sealing surface, wherein the first sidewall and the second sidewall are parallel, and wherein the first sidewall and the second sidewall define an oblique angular relationship to the centerline of the combustor;
- a sealing system first end coupled to the seal housing;
- a sealing system second and connected to a structural member and disposed radially inward of a turbine nozzle;
- and
- a seal ring positioned at least partially within the groove in the seal housing, wherein the seal ring acts upon the inside surface, and wherein the seal ring defines a seal contact surface for forming a seal with the oblique sealing surface of the combustor.
A combustion chamber defining a centerline, including a structural member and a turbine nozzle, wherein the turbine nozzle includes an inner band defining a curved portion, the combustion chamber comprising:
- a liner having an inside surface, the inside surface defining an oblique sealing surface, the oblique sealing surface defining an annular shape about an axial centerline of a turbine engine and an oblique angle with the axial centerline of the turbine engine;
- a seal housing disposed radially inward of the inside surface, wherein the seal housing is annular about the axial centerline of the turbine engine and includes a groove that is defined by a first sidewall, a second sidewall, and an end wall connecting the first sidewall and the second sidewall, wherein the first sidewall and the second sidewall are parallel, and wherein the first sidewall and the second sidewall define an oblique angular relationship to the centerline of the combustion chamber;
- and
- a seal ring positioned at least partially within the groove in the seal housing, wherein the seal ring is positioned at least partially between the seal housing and the oblique sealing surface, wherein the seal ring acts upon the inside surface, and wherein the seal ring defines a seal contact surface for forming a seal with the oblique sealing surface of the liner.
Dependencies are inferred from the claim text.