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US 9,851,008 B2Granted
Seal land for static structure of a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsSteven D. Porter, Jonathan P. Burt, Jonathan J. Jakiel, Amy M. Gordon, Shelton O. Duelm
Life of this patent
Estimating the term…
Abstract
A seal land for a gas turbine engine can include a seal body circumferentially extending about a longitudinal centerline axis. The seal body includes at least one sealing surface that extends in a plane that is transverse to the longitudinal centerline axis.
Claims23
A seal land for a gas turbine engine, comprising:
- a seal body of a mid-turbine frame circumferentially extending about a longitudinal centerline axis, said seal body including a leading edge portion, a trailing edge portion, and an inner radial surface and an outer radial surface that extend between said leading edge portion and said trailing edge portion, said seal body is tapered between said trailing edge portion and said leading edge portion, wherein at least one of said inner radial surface and said outer radial surface includes at least one sealing surface in sealing contact with another sealing surface of a separate seal, and wherein both said inner radial surface and said outer radial surface of said seal body extend in a plane that is transverse to said longitudinal centerline axis.
A static structure for a gas turbine engine, comprising:
- at least one airfoil that extends between an inner platform and an outer platform that are circumferentially disposed about a longitudinal centerline axis of said static structure, wherein at least one of said inner platform and said outer platform extend at a first angle relative to said longitudinal centerline axis;
- and
- at least one seal land extending from at least one of said inner platform and said outer platform, wherein said at least one seal land includes at least one sealing surface positioned at either a radially inner surface or a radially outer surface of said at least one seal land, said at least one sealing surface extending at a second angle relative to said longitudinal centerline axis, and said first angle and said second angle are transverse to said longitudinal centerline axis, and said at least one seal land including a tapering width that continuously increases in a direction from a leading edge of said at least one seal land toward a trailing edge of said at least one seal land, and wherein both said radially inner surface and said radially outer surface extend in a plane that is transverse to said longitudinal centerline axis.
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;
- a static structure configured as a mid-turbine frame positioned between a first portion and a second portion of said turbine section, wherein said static structure includes a multitude of airfoils and at least one seal land that extends from a platform of said multitude of airfoils, wherein said platform and at least one sealing surface of said at least one seal land axially extend at a transverse angle relative to an engine longitudinal centerline axis of the gas turbine engine, and said at least one sealing surface is in sealing contact with another sealing surface of a separate seal, and wherein a seal body of said at least one seal land is tapered between a trailing edge portion and a leading edge portion of said seal body and includes an inner radial surface and an outer radial surface that extend in a plane that is transverse to said engine longitudinal centerline axis, and wherein either the inner radial surface or the outer radial surface includes the at least one sealing surface.
1 more element
Dependencies are inferred from the claim text.