Deflector for conduit inlet within a combustor section plenum

Patent metadata

Field	Value
Publication number	US-2022018540-A1
Application number	US-202016929673-A
Country	US
Kind code	A1
Filing date	Jul 15, 2020
Priority date	Jul 15, 2020
Publication date	Jan 20, 2022
Grant date	—

Abstract

An assembly is provided for a gas turbine engine. This assembly includes a combustor wall, a case and an inlet. The combustor wall is configured with a quench aperture. The case is displaced from the combustor wall such that a plenum is formed by and extends between the combustor wall and the case. The case includes a case wall, a deflector and a conduit. The deflector projects out from the case wall into the plenum towards the combustor wall. The deflector is arranged upstream of the quench aperture. The inlet to the conduit is arranged next to and downstream of the deflector.

First claim

1 . An assembly for a gas turbine engine, the assembly comprising:
a combustor wall configured with a quench aperture; a case displaced from the combustor wall such that a plenum is formed by and extends between the combustor wall and the case; the case comprising a case wall, a deflector and a conduit; the deflector projecting out from the case wall into the plenum towards the combustor wall, and the deflector arranged upstream of the quench aperture; and an inlet to the conduit arranged next to and downstream of the deflector, and the inlet to the conduit arranged axially forward of the quench aperture.

2 . The assembly of claim 1 , wherein the case is displaced radially inward of the combustor wall relative to an axis of the gas turbine engine.

3 . The assembly of claim 1 , wherein the deflector is arranged axially forward of the quench aperture relative to an axis of the gas turbine engine.

4 . The assembly of claim 1 , wherein the deflector is axially overlapped by an axial forwardmost half of the combustor wall.

5 . The assembly of claim 1 , wherein the deflector comprises a ramped deflector.

6 . The assembly of claim 1 , wherein the deflector is cantilevered from the case wall.

7 . The assembly of claim 1 , wherein the deflector projects out from the case wall in a direction that includes a radial outward component and an axially aft component relative to an axis of the gas turbine engine.

8 . The assembly of claim 1 , wherein the deflector is configured such that gas flowing within the plenum turns more than ninety degrees around a distal end of the deflector before entering the inlet.

9 . The assembly of claim 1 , wherein the case further includes a gate projecting out from the conduit, and the gate is configured to reduce or prevent recirculating gas within the plenum from flowing into the inlet.

10 . The assembly of claim 9 , wherein
the deflector has a deflector chord line that is angularly offset from an axis by a deflector angle; and the gate has a gate chord line that is angularly offset from the axis by a gate angle that is equal to the deflector angle.

11 . The assembly of claim 9 , wherein
the deflector has a deflector chord line that is angularly offset from an axis by a deflector angle; and the gate has a gate chord line that is angularly offset from the axis by a gate angle that is different than the deflector angle.

12 . The assembly of claim 9 , wherein the gate is connected to the conduit at the inlet.

13 . The assembly of claim 9 , wherein the gate is cantilevered from the conduit.

14 . The assembly of claim 1 , wherein the inlet is arranged upstream of the quench aperture.

15 . The assembly of claim 1 , further comprising a tangential onboard injector nozzle fluidly coupled with the plenum through the conduit.

16 . The assembly of claim 1 , further comprising:
a turbine component; the conduit fluidly coupling a passage in the turbine component with the plenum.

17 . The assembly of claim 1 , further comprising:
an annular combustor comprising an inner combustor wall, an outer combustor wall and a bulkhead, wherein the inner combustor wall comprises the combustor wall; the bulkhead extending radially between and connected to the inner combustor wall and the outer combustor wall.

18 . An assembly for a gas turbine engine, the assembly comprising:
a combustor wall extending axially along and circumferentially about an axial centerline; a case radially displaced from the combustor wall, wherein a plenum extends radially from the case to the combustor wall; the case comprising a case wall, a deflector and a conduit; the deflector projecting out from the case wall, into the plenum and towards the combustor wall, to an aft distal end of the deflector, and the aft distal end of the deflector axially overlapped by an axially forward half of the combustor wall; and an inlet to the conduit arranged at the aft distal end of the deflector.

19 . An assembly for a gas turbine engine, the assembly comprising:
a combustor wall extending axially along and circumferentially about an axial centerline of the gas turbine engine; a case radially displaced from the combustor wall, wherein a plenum extends radially between the case and the combustor wall; the case comprising a case wall, a deflector, a conduit and a gate; the deflector projecting out from the case wall, in an axial aft direction, into the plenum towards the combustor wall; an inlet of the conduit arranged axially between the deflector and the gate; and the gate projecting out from the conduit, in the axial aft direction, into the plenum towards the combustor wall, and the gate configured to reduce or prevent recirculating gas within the plenum from flowing into the inlet.

20 . The assembly of claim 19 , wherein an axially forward end of the gate is arranged axially upstream of a quench aperture in the combustor wall.

Assignees

• Raytheon Tech Corp

Inventors

• Prenter Robin
• Lundgreen Ryan

Classifications

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/002 Primary

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

• F23R3/005

  Combined with pressure or heat exchangers · CPC title