Swirl stabilized vaporizer combustor

Patent metadata

Field	Value
Publication number	US-10767865-B2
Application number	US-201715603396-A
Country	US
Kind code	B2
Filing date	May 23, 2017
Priority date	Jun 13, 2016
Publication date	Sep 8, 2020
Grant date	Sep 8, 2020

Abstract

A gas turbine engine and a combustor are described herein. The combustor includes a fuel vaporizer coupled to a combustor wall, which extends into a combustion chamber. A fuel injector having a nozzle extends within a portion of the fuel vaporizer. A dome swirler is coupled to an upstream dome portion of the combustor wall. The swirler surrounds a heat shield, which may have a concaved body. The outlet end of the fuel vaporizer is disposed over the heat shield, which may be over the central zone of the heat shield, to face the heat shield. The fuel vaporizer may be coupled to the combustor wall and disposed outside the swirler. Fuel and air mixture exits the vaporizer and impinges against the heat shield and is then combined with the swirler air to become part of the primary zone recirculation.

First claim

What is claimed is:

1. A combustor for a gas turbine engine, comprising:
a combustor wall including an upstream wall portion interconnected between an inner wall structure and an outer wall structure to define a combustion chamber, the combustion chamber defined about a longitudinal centerline of the combustor;
a vaporizer tube having a first end opening and a second end opening;
a fuel injector extending through the first end opening along a portion of the vaporizer tube, the fuel injector having an outer cross-sectional area sized smaller than an inner cross-sectional area of the first end opening and the vaporizer tube to define a compressed air passageway into the vaporizer tube;
a swirler coupled to the upstream wall portion, wherein the swirler comprises an axial swirler; and
a heat shield surrounded by the swirler;
wherein the vaporizer tube is coupled to a port formed in the upstream wall portion outside the swirler and is extended within the combustion chamber, and the vaporizer tube is shaped to place the second end opening over the heat shield, wherein the second end opening faces the heat shield such that a fuel-air mixture exiting the second end opening impinges against the heat shield, and the swirler comprises a plurality of swirler vanes arranged in the swirler to create toroidal recirculation air that mixes with the impinging fuel-air mixture between the second end opening and the heat shield,
wherein the swirler, the heat shield, and the second end opening are co-axially aligned with the longitudinal center line of the combustor.

2. The combustor of claim 1 , wherein the heat shield includes a concaved body having an upstream side and a downstream side, and wherein the upstream side of the concaved body is configured to direct a flow of compressed air to the swirler, and the fuel-air mixture impinges against the downstream side.

3. The combustor of claim 2 , further comprising a diffuser inlet positioned to direct compressed air linearly at the upstream side of the heat shield, the upstream side configured to divert the compressed air around the heat shield toward the surrounding swirler for receipt by the swirler vanes.

4. The combustor of claim 2 , wherein the concaved body of the heat shield has a circular periphery defined about a heat shield axis.

5. The combustor of claim 4 , wherein an axis of the vaporizer tube at the second end opening is coaxial with the heat shield axis and the swirler.

6. The combustor of claim 1 , wherein the vaporizer tube is defined by a main trunk portion and a branch portion extending radially from the main trunk portion, an end of the main trunk portion coextensive with the first end opening and an end of the branch portion coextensive with the second end opening, wherein the fuel injector extends within the main trunk portion of the vaporizer tube.

7. The combustor of claim 6 , wherein the heat shield includes a concaved body having a circular periphery defined about a heat shield axis, and the swirler includes an inner band extending along the circular periphery of the concaved body of the heat shield, an outer band, and the plurality of swirler vanes are disposed in an annular arrangement between the inner and outer bands.

8. The combustor of claim 6 , wherein the main trunk portion is disposed about a linear portion of a vaporizer axis, and the branch portion extends away from the linear portion of the vaporizer axis in a curved fashion to dispose the second end opening in a spaced relationship with the heat shield.

9. The combustor of claim 1 , wherein the swirler is a first swirler, the heat shield is a first heat shield, and the vaporizer tube includes another second end opening, the combustor further comprising a second swirler coupled to the upstream wall portion adjacent the first swirler, a second heat shield disposed along the upstream wall portion, surrounded by the second swirler, wherein the vaporizer tube is coupled to the upstream wall portion between the first swirler and the second swirler, wherein the vaporizer tube is shaped to place one of the second end openings over a central zone of the first heat shield to face the first heat shield, and to place the other of the second end openings over a central zone of the second heat shield to face the second heat shield.

10. The combustor of claim 9 , wherein the vaporizer tube is defined by a main trunk portion and a first branch portion and a second branch portion each extending radially from the main trunk portion, an end of the main trunk portion is coextensive with the first end opening, an end of the first branch portion is coextensive with one of the second end openings, and an end of the second branch portion is coextensive with the other of the second end openings, wherein the fuel injector extends within the main trunk portion of the vaporizer tube.

11. The combustor of claim 1 , wherein the port is formed in the upstream wall portion offset from the longitudinal center-line of the combustor.

12. A gas turbine engine, comprising:
a combustor to receive compressed air from a compressor and to deliver combustion products to a turbine, the combustor having a combustor wall including an upstream wall portion interconnected between an inner wall structure and an outer wall structure to define a combustion chamber, the combustion chamber defined about a longitudinal centerline of the combustor;
a fuel vaporizer tube coupled to the combustor wall extending into the combustion chamber, the vaporizer tube having a first end opening and a second end opening;
a swirler coupled to the upstream wall portion, the swirler comprising an axial swirler having a plurality of swirler vanes arranged to create toroidal recirculation air; and
a heat shield coaxially positioned with respect to the swirler as part of the upstream wall portion, wherein the heat shield is surrounded by the swirler, wherein the second end opening of the vaporizer tube is disposed over the heat shield and faces the heat shield so that a fuel-air mixture exiting the second end impinges against the heat shield and combines, between the heat shield and the second end, with the toroidal recirculation air,
wherein the swirler, the heat shield, and the second end opening are co-axially aligned with the longitudinal center line of the combustor.

13. The combustor of claim 12 , wherein the swirler vanes are skewed relative to a swirler axis to create, with the toroidal recirculation air, a toroidal recirculation zone between the second end opening and the heat shield, the toroidal recirculation zone including a low pressure zone in which at least some of the combustion products are re-circulated.

14. The gas turbine engine of claim 12 , further comprising a fuel injector having a nozzle extending within a portion of the vaporizer tube through the first end opening, wherein the nozzle of the fuel injector has an outer cross-sectional area sized smaller than an inner cross-sectional area of the first end opening and the vaporizer tube to allow compressed air to enter the vaporizer tube where it is mixed with fuel delivered from the nozzle to define a fuel-air mixture to impinge against the heat shield when the fuel-air mixture exits the second end opening of the vaporizer tube.

15. The gas turbine engine of claim 14 , wherein the vaporizer tube is coupled to the upstream wall portion of the combustor wall radially outside the swirler.

16. The gas turbine engine of claim 15 , wherein the heat shield includes a concaved body to deflect the impinging fuel-air mixture radially outward and downstream to further combine with compressed

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Roesler Timothy C

Classifications

• F23D11/406

  Flame stabilising means, e.g. flame holders · CPC title

• F23R3/32

  being tubular · CPC title

• F23D11/441

  Vaporising devices incorporated with burners · CPC title

• F23D11/402

  Mixing chambers downstream of the nozzle · CPC title

• F23R3/30

  comprising fuel prevapourising devices · CPC title