Deflector for conduit inlet within a combustor section plenum
AssigneeRaytheon Technologies Corporation
InventorsRobin Prenter, Ryan Lundgreen
Life of this patent
Estimating the term…
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.
Claims20
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.
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.
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.
Dependencies are inferred from the claim text.