Axisymmetric offset of three-dimensional contoured endwalls

Patent metadata

Field	Value
Publication number	US-2016290645-A1
Application number	US-201415037914-A
Country	US
Kind code	A1
Filing date	Nov 10, 2014
Priority date	Nov 21, 2013
Publication date	Oct 6, 2016
Grant date	—

Abstract

An engine component includes a gaspath wall defining a radially outward facing gaspath surface and an opposed non-gaspath surface. The gaspath surface defines a non-axisymmetric contour with a respective point of minimum radius for each axial position. The non-gaspath surface defines an axisymmetric contour. Each axial position on the axisymmetric contour defines a circle offset from the respective point of minimum radius of the gaspath surface by a predetermined minimum wall thickness. The predetermined minimum wall thickness is substantially constant as a function of axial position. A similar predetermined minimum wall thickness and axisymmetric non-gaspath surface contour can be applied to a gaspath wall with a radially inward facing gaspath surface defining a non-axisymmetric contour.

First claim

What is claimed is:

1 . An engine component comprising:
a gaspath wall defining a radially outward facing gaspath surface and an opposed non-gaspath surface, wherein the gaspath surface defines a non-axisymmetric contour with a respective point of minimum radius for each axial position, and wherein the non-gaspath surface defines an axisymmetric contour wherein each axial position on the axisymmetric contour defines a circle offset from the respective point of minimum radius of the gaspath surface by a predetermined minimum wall thickness, wherein the predetermined minimum wall thickness is a function of axial position.

2 . An engine component as recited in claim 1 , wherein the predetermined minimum wall thickness is substantially constant as a function of axial position.

3 . An engine component as recited in claim 1 , wherein the gaspath wall includes a plurality of annular segments defining an inner wall for an annular flow path.

4 . An engine component as recited in claim 3 , wherein the gaspath wall is an endwall wherein each annular segment includes one of a turbomachine blade and a turbomachine vane extending radially outward therefrom.

5 . An engine component as recited in claim 1 , wherein the gaspath wall is an inner wall for at least one of a fan, a compressor, a combustor, a turbine, an inlet, a diffuser, a transition duct, a mid-turbine frame, a turbine exhaust case, an exhaust duct, an afterburner duct, a nacelle, a secondary flow system, and a nozzle for a gas turbine engine.

6 . An engine component as recited in claim 1 , wherein the gaspath wall is a portion of an inner wall for at least one of a fan, a compressor, a combustor, a turbine, an inlet, a diffuser, a transition duct, a mid-turbine frame, a turbine exhaust case, an exhaust duct, an afterburner duct, a nacelle, a secondary flow system, and a nozzle for a gas turbine engine.

7 . An engine component as recited in claim 1 , wherein the gaspath wall is an annular segment for forming a portion of an inner wall for an annular flow path with a plurality of similar annular segments.

8 . An engine component as recited in claim 7 , wherein the gaspath wall is an annular endwall segment and includes one of a turbomachine vane and a turbomachine blade extending radially outward therefrom.

9 . An engine component comprising:
a gaspath wall defining a radially inward facing gaspath surface and an opposed non-gaspath surface, wherein the gaspath surface defines a non-axisymmetric contour with a respective point of maximum radius for each axial position, and wherein the non-gaspath surface defines an axisymmetric contour wherein each axial position on the axisymmetric contour defines a circle offset from the respective point of maximum radius of the gaspath surface by a predetermined minimum wall thickness, wherein the predetermined minimum wall thickness is a function of axial position.

10 . An engine component as recited in claim 9 , wherein the predetermined minimum wall thickness is substantially constant as a function of axial position.

11 . An engine component as recited in claim 9 , wherein the gaspath wall includes a plurality of annular segments defining an outer wall for an annular flow path.

12 . An engine component as recited in claim 11 , wherein the gaspath wall is an endwall wherein each annular segment includes one of a turbomachine vane and a turbomachine blade extending radially inward therefrom.

13 . An engine component as recited in claim 9 , wherein the gaspath wall is an outer wall for at least one of a fan, a compressor, a combustor, a turbine, an inlet, a diffuser, a transition duct, a mid-turbine frame, a turbine exhaust case, an exhaust duct, an afterburner duct, a nacelle, a secondary flow system, and a nozzle for a gas turbine engine.

14 . An engine component as recited in claim 9 , wherein the gaspath wall is a portion of an outer wall for at least one of a fan, a compressor, a combustor, a turbine, an inlet, a diffuser, a transition duct, a mid-turbine frame, a turbine exhaust case, an exhaust duct, an afterburner duct, a nacelle, a secondary flow system, and a nozzle for a gas turbine engine.

15 . An engine component as recited in claim 9 , wherein the gaspath wall is an annular segment for forming a portion of an outer wall for an annular flow path with a plurality of similar annular segments.

16 . An engine component as recited in claim 15 , wherein the gaspath wall is an annular endwall segment and includes one of a turbomachine vane and a turbomachine blade extending radially inward therefrom.

17 . An engine component comprising:
a first gaspath wall defining a radially outward facing first gaspath surface and an opposed first non-gaspath surface, wherein the first gaspath surface defines a first non-axisymmetric contour with a respective point of minimum radius for each axial position, and wherein the first non-gaspath surface defines a first axisymmetric contour wherein each axial position on the first axisymmetric contour defines a circle offset from the respective point of minimum radius of the first gaspath surface by a first predetermined minimum wall thickness, wherein the first predetermined minimum wall thickness is substantially constant as a function of axial position; and a second gaspath wall radially opposed to the first gaspath wall and defining a radially inward facing second gaspath surface and an opposed second non-gaspath surface, wherein the second gaspath surface defines a second non-axisymmetric contour with a respective point of maximum radius for each axial position, and wherein the second non-gaspath surface defines a second axisymmetric contour wherein each axial position on the second axisymmetric contour defines a circle offset from the respective point of maximum radius of the second gaspath surface by a second predetermined minimum wall thickness, wherein the second predetermined minimum wall thickness is substantially constant as a function of axial position.

18 . An engine component as recited in claim 17 , wherein at least one of the first and second gaspath walls includes a plurality of annular segments defining a wall for an annular flow path.

19 . An engine component as recited in claim 17 , wherein the first and second predetermined minimum wall thicknesses are the same.

20 . An engine component as recited in claim 17 , wherein the first and second predetermined minimum wall thicknesses are different from one another.

Assignees

• United Technologies Corp

Inventors

• Carr Jesse M

Classifications

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title

• F05D2250/184

  sinusoidal · CPC title

• F05D2220/32

  in gas turbines · CPC title