Combustor for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-12146660-B2
Application number	US-202117340654-A
Country	US
Kind code	B2
Filing date	Jun 7, 2021
Priority date	Jun 7, 2021
Publication date	Nov 19, 2024
Grant date	Nov 19, 2024

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 liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.

First claim

We claim:

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 defining an outer surface and an aft end;
an aft liner segment defining a forward end axially spaced from and adjacent to the aft end of the forward liner segment and defining a dilution slot therebetween, wherein the forward liner segment and the aft liner segment at least partially define a combustion chamber; and
an intermediate member, the intermediate member comprising a body partially disposed within the dilution slot, the body defining a first engagement feature having a first sealing portion, a second engagement feature having a second sealing portion, a radial portion, a longitudinal portion, and a fence, wherein the first sealing portion is configured to slidably seal against the outer surface of the forward liner, the second sealing portion including a first sealing interface extending across an outside of the aft liner segment, and a second sealing interface extending across an inside of the aft liner segment.

2. The combustor of claim 1 , wherein the radial portion and the longitudinal portion define a support, wherein the support is integral with the body of the intermediate member, and wherein the support is configured to engage with a casing of the combustor.

3. The combustor of claim 1 , wherein the intermediate member fence extends radially inward from the inside of the aft liner segment into the combustion chamber in the radial direction, the fence being configured to direct cooling medium into the combustion chamber.

4. The combustor of claim 1 , wherein the first sealing portion comprises a piston seal engaged with the outer surface of the forward liner segment.

5. The combustor of claim 4 , wherein the piston seal comprises at least one purging hole configured to permit purging of excess cooling medium before entering the combustion chamber.

6. The combustor of claim 1 , wherein the second sealing portion includes a piston seal disposed between the first sealing interface and the outside of the aft liner segment.

7. The combustor of claim 1 , wherein the second sealing portion includes a piston seal disposed between the second sealing interface and the inside of the aft liner segment.

8. The combustor of claim 1 , wherein the first engagement feature defines a window, wherein the window extends axially between the first sealing portion and the radial portion of the body of the intermediate member.

9. The combustor of claim 1 , wherein the radial portion of the body of the intermediate member defines a window, wherein the window extends radially between the first engagement feature and the longitudinal portion of the body of the intermediate member.

10. The combustor of claim 1 , wherein the first engagement feature defines a stop feature, wherein the stop feature extends into the dilution slot between the aft end of the forward liner and the fence.

11. The combustor of claim 1 , wherein the second engagement feature defines a stop feature, wherein the forward end of the aft liner segment is axially spaced from the stop feature.

Assignees

• Gen Electric

Inventors

• Ganiger Ravindra Shankar
• Nath Hiranya Kumar
• Kirtley Daniel J
• Birmaher Shai
• Vanapalli Veeraraju
• Sampath Karthikeyan
• Ghiya Deepak
• Vukanti Perumallu
• Wankhade Rajendra Mahadeorao
• Naik Pradeep

Classifications

• F05D2240/55

  Seals · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R3/52

  Toroidal combustion chambers · CPC title