Turbine engine assembly

Patent metadata

Field	Value
Publication number	US-2021087942-A1
Application number	US-202016939435-A
Country	US
Kind code	A1
Filing date	Jul 27, 2020
Priority date	Sep 17, 2019
Publication date	Mar 25, 2021
Grant date	—

Abstract

An assembly for a turbine engine can include a monolithic body with an inner band and an outer band radially spaced from the inner band, a pocket surface in one of the inner or outer bands defining a recess, and an airfoil with a first end radially extending from the other of the inner or outer bands.

First claim

What is claimed is:

1 . An assembly for a turbine engine comprising:
a monolithic body, comprising:
an inner band and an outer band radially spaced from the inner band;
a pocket surface in one of the inner or outer bands defining a recess; and
an airfoil comprising an outer wall defining a pressure side and a suction side, a first end radially extending from the other of the inner or outer bands, and a second end radially extending into the recess to define a gap between the airfoil and the one of the inner or outer bands.

2 . The assembly of claim 1 , further comprising a support structure at least partially closing the gap and coupled to at least one of the second end or the pocket surface.

3 . The assembly of claim 2 wherein the support structure comprises:
an airfoil recess in the second end; and
a pin extending into the one of the inner or outer bands and received in the airfoil recess to at least partially close the gap.

4 . The assembly of claim 2 wherein the support structure comprises a clip spanning the gap and having a first clip end retained by the second end of the airfoil.

5 . The assembly of claim 4 wherein the clip further comprises a spring clip having a second clip end retained by the one of the inner or outer bands.

6 . The assembly of claim 5 wherein the second end extends fully through the one of the inner or outer bands.

7 . The assembly of claim 4 wherein the clip further comprises a T-shaped body with a first leg terminating in the first clip end and extending into the second end of the airfoil.

8 . The assembly of claim 7 wherein the T-shaped body comprises a second leg extending perpendicular to the first leg and coupled to the one of the inner or outer bands.

9 . The assembly of claim 8 , further comprising a labyrinth seal at least partially defined by the gap and the first leg of the T-shaped body.

10 . The assembly of claim 2 wherein the support structure comprises at least one curvilinear damper connecting the second end of the airfoil and the one of the inner or outer bands.

11 . The assembly of claim 2 wherein the support structure extends along an entire axial length of the airfoil.

12 . The assembly of claim 2 wherein the support structure is coupled by at least one coupling point to the at least one of the second end or the pocket surface.

13 . The assembly of claim 12 wherein the support structure is configured to break away at the at least one coupling point to define a narrowed gap, smaller than the gap, between the second end and the pocket surface.

14 . The assembly of claim 2 wherein the support structure comprises a protrusion defined by the pocket surface and contacting the second end of the airfoil.

15 . The assembly of claim 2 wherein the support structure contacts the suction side of the airfoil.

16 . The assembly of claim 2 wherein the support structure fully closes the gap.

17 . The assembly of claim 1 wherein the airfoil comprises a static vane in one of a compressor or a turbine section in the turbine engine.

18 . The assembly of claim 1 wherein the monolithic body further comprises a vane extending fully between the inner band and the outer band.

19 . The assembly of claim 18 wherein the monolithic body further comprises a pair of airfoils and a corresponding pair of recesses in the one of the inner or outer bands, the pair of airfoils having first ends radially extending from the other of the inner or outer bands and second ends radially extending into the pair of recesses, with the vane positioned circumferentially between each airfoil in the pair of airfoils.

20 . A turbine engine, comprising:
a compressor, a combustor, and a turbine in axial arrangement; and an assembly in at least one of the compressor or the turbine, the assembly having a monolithic body comprising:
an inner band and an outer band radially spaced from the inner band;
a pocket surface in one of the inner or outer bands defining a recess; and
an airfoil comprising an outer wall defining a pressure side and a suction side, a first end radially extending from the other of the inner or outer bands, and a second end radially extending into the recess to define a gap between the airfoil and the one of the inner or outer bands.

21 . The turbine engine of claim 20 , further comprising a support structure at least partially closing the gap, wherein the support structure comprises one of a pin, a clip, a curvilinear damper, or a protrusion.

22 . An assembly for a turbine engine comprising a monolithic body having an inner band, an outer band radially spaced from the inner band, a recess in one of the inner or outer bands, and a vane having a root at the other of the inner or outer bands and a second tip located within the recess and free of the one of the inner or outer bands.

Assignees

• General Electric Company Polska Sp Zoo

Inventors

• Kulinski Piotr Jerzy
• Berdowski Tomasz Edward

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F01D9/041 Primary

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

• F01D5/225

  by shrouding · CPC title