Combustor for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2022390112-A1
Application number	US-202117340703-A
Country	US
Kind code	A1
Filing date	Jun 7, 2021
Priority date	Jun 7, 2021
Publication date	Dec 8, 2022
Grant date	—

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 including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

First 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 liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

2 . The combustor of claim 1 , wherein the liner comprises a forward liner segment and an aft liner segment, and wherein the dilution slot is disposed between the forward and aft liner segments.

3 . The combustor of claim 2 , wherein at least one of the one or more guides is integral with at least one of the forward and aft liner segments.

4 . The combustor of claim 1 , wherein the one or more guides comprise an inclined leading edge surface that is angularly offset from the radial direction by an angle, as, that is at least 1°.

5 . The combustor of claim 1 , wherein the one or more guides extend outward from the liner in the radial direction.

6 . The combustor of claim 1 , wherein at least one of the one or more guides comprises a scooped interface.

7 . The combustor of claim 1 , wherein the one or more guides comprise a leading edge surface defining one or more rows of windows extending around the combustor.

8 . The combustor of claim 1 , further comprising a fence extending in the radial direction into the combustion chamber through the dilution slot.

9 . The combustor of claim 8 , wherein at least one of the one or more guides is at least partially disposed upstream of the fence.

10 . The combustor of claim 1 , wherein the dilution slot comprises a plurality of dilution slots extending around the combustion chamber in the circumferential direction.

11 . A liner 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 liner comprising:
an annular body configured to at least partially define a combustion chamber of the combustor, wherein the annular body comprises a dilution slot extending to the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

12 . The liner of claim 11 , wherein the one or more guides are integral with the annular body.

13 . The liner of claim 11 , wherein the one or more guides include one or more rows of cooling holes.

14 . The liner of claim 13 , wherein the forward liner segment and aft liner segment are coupled together through a wavy annular body disposed between the forward and aft liner segments in the radial direction.

15 . The liner of claim 13 , wherein at least one of the one or more guides is integral with at least one of the forward and aft liner segments.

16 . The liner of claim 11 , wherein at least one of the one or more guides comprises a scooped interface.

17 . 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 liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and a scooped interface configured to redirect cooling medium into the dilution slot, the scooped interface defining a scooped surface configured to form a film of airflow into the combustor.

18 . The combustor of claim 17 , wherein the scooped interface extends from the liner in a radially outward direction, and wherein the scooped interface is configured to redirect cooling medium to a fence of the combustor, the fence extending into the combustion chamber.

19 . The combustor of claim 17 , wherein the scooped interface comprises one or more windows configured to pass cooling medium to the scooped surface, and wherein the one or more windows are arranged in one or more rows extending in the circumferential direction.

20 . The combustor of claim 17 , wherein the scooped interface is coupled with an aft liner segment of the liner, and wherein the scooped interface is configured to move relative to a forward liner segment of the liner.

Assignees

• Gen Electric

Inventors

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

Classifications

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/00005

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

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R2900/00001

  Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses · CPC title