Combustor for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-12578095-B2
Application number	US-202418585509-A
Country	US
Kind code	B2
Filing date	Feb 23, 2024
Priority date	Jun 7, 2021
Publication date	Mar 17, 2026
Grant date	Mar 17, 2026

Abstract

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

First claim

The invention claimed is:

1 . A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising:
a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward liner segment and the aft liner segment at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward liner segment and the aft liner segment and extending in the circumferential direction, wherein the intermediate member comprises a plurality of spokes extending from the forward liner segment and the aft liner segment, each of the plurality of spokes including a first arm and a second arm, the first arm having a first arm non-linear portion at a first end of the first arm, the first arm non-linear portion extending from the forward liner segment radially outward, and a first arm linear portion at a second end of the first arm, the first arm linear portion extending radially outward from the first arm non-linear portion, the second end of the first arm being axially angled toward the second arm at the second end of the first arm, the second arm having a second arm non-linear portion at a first end of the second arm, the second arm non-linear portion extending from the aft liner segment radially outward, and a second arm linear portion at a second end of the second arm, the second arm linear portion extending radially outward from the second arm non-linear portion, the second end of the second arm being axially angled toward the first arm at the second end of the second arm such that the first end of the first arm and the first end of the second arm are axially spaced from each other, and the second end of the first arm and the second end of the second arm contact each other.

2 . The combustor of claim 1 , wherein the intermediate member comprises an annular support ring and the plurality of spokes each extends from the annular support ring.

3 . The combustor of claim 1 , wherein at least one spoke of the plurality of spokes further comprises a feature configured to tune the at least one spoke.

4 . The combustor of claim 1 , further comprising a dilution slot extending between the forward liner segment and the aft liner segment, wherein the plurality of spokes extends over the dilution slot such that the first end of the first arm is on a first axial side of the dilution slot, the first end of the second arm is on a second axial side of the dilution slot, and the second end of the first arm and the second end of the second arm are axially aligned with the dilution slot.

5 . The combustor of claim 1 , further comprising a case at least partially surrounding the combustor, wherein the plurality of spokes extends between the case and the forward liner segment and the aft liner segment.

6 . The combustor of claim 5 , wherein the intermediate member comprises an annular support ring extending in the circumferential direction, wherein the plurality of spokes is coupled to the case with the annular support ring.

7 . The combustor of claim 6 , wherein the plurality of spokes and the annular support ring are a single, integral piece.

8 . The combustor of claim 6 , wherein the annular support ring is fastened to the case.

9 . The combustor of claim 8 , further comprising a flange fastened to the case, the annular support ring coupled to the flange.

10 . The combustor of claim 6 , wherein the forward liner segment, the aft liner segment, or both, include a ceramic material, and wherein the plurality of spokes is separate from the forward liner segment and the aft liner segment and extend from the case.

11 . The combustor of claim 1 , wherein at least one spoke of the plurality of spokes has a hook joint having a generally rounded U-shaped or V-shaped cross-sectional profile.

12 . The combustor of claim 1 , wherein one or both of the first arm and the second arm are tuned to control axial deformation, radial deformation, or both between the forward liner segment and the aft liner segment.

13 . The combustor of claim 10 , wherein the first arm non-linear portion, the second arm non-linear portion, or both, of at least one spoke of the plurality of spokes control a stiffness of the at least one spoke.

14 . The combustor of claim 1 , wherein each of the plurality of spokes is discrete and separate from each other.

15 . An intermediate member for a combustor of a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor having a forward liner segment and an aft liner segment, the forward liner segment and the aft liner segment at least partially defining a combustion chamber, the intermediate member comprising:
a plurality of spokes extending from the forward liner segment and the aft liner segment, each of the plurality of spokes including:
a first arm extending from a first end to a second end, the first arm having a first arm non-linear portion at the first end of the first arm and a first arm linear portion at the second end of the first arm; and
a second arm extending from a first end to a second end, the second arm having a second arm non-linear portion at the first end of the second arm and a second arm linear portion at the second end of the second arm,

wherein the first arm non-linear portion extends from the forward liner segment radially outward, the first arm linear portion extends radially outward from the first arm non-linear portion, and the second end of the first arm is axially angled toward the second arm at the second end of the first arm, the second arm non-linear portion extends from the aft liner segment radially outward, the second arm linear portion extends radially outward from the second arm non-linear portion, and the second end of the second arm is axially angled toward the first arm at the second end of the second arm such that the first end of the first arm and the first end of the second arm are axially spaced from each other, and the second end of the first arm and the second end of the second arm contact each other.

16 . The intermediate member of claim 15 , wherein at least one spoke of the plurality of spokes further comprises a feature configured to tune the at least one spoke.

17 . The intermediate member of claim 15 , wherein the gas turbine engine includes a dilution slot extending between the forward liner segment and the aft liner segment, wherein the plurality of spokes extends over the dilution slot such that first end of the first arm is on a first axial side of the dilution slot, the first end of the second arm is on a second axial side of the dilution slot, and the second end of the first arm and the second end of the second arm are axially aligned with the dilution slot.

18 . The intermediate member of claim 15 , wherein the gas turbine engine includes a case at least partially surrounding the combustor, wherein the plurality of spokes extends between the case and the forward liner segment and the aft liner segment.

19 . The intermediate member of

Assignees

• Gen Electric

Inventors

• Sampath Karthikeyan
• Naik Pradeep
• Vanapalli Veeraraju
• Vukanti Perumallu
• Birmaher Shai
• Kirtley Daniel J
• Ghiya Deepak
• Rangrej Rimple Rakeshkumar
• Singh Saket
• Ganiger Ravindra Shankar
• Nath Hiranya Kumar
• Benjamin Michael Anthony
• Wankhade Rajendra Mahadeorao

Classifications

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title