Gas turbine engine and annular combustor with swirler

Patent metadata

Field	Value
Publication number	US-10295191-B2
Application number	US-201113341941-A
Country	US
Kind code	B2
Filing date	Dec 31, 2011
Priority date	Dec 31, 2011
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

A combustor is provided in which a fuel and working fluid can be injected in an annulus. In one form the fuel and working fluid is circumferentially flowed within the annulus and traverses the annulus in an axial direction from one side to another side where the flow exits. The working fluid and air can be co-axially admitted to the combustor and in one form the working fluid can be swirled about the fuel dispensed from a fuel injector. The combustor can provide for a rich burning zone. In one embodiment the combustor is configured as an inter-turbine combustor having an outlet at one axial side of the combustor. A lean burn region can be created within a flow path of the turbine.

First claim

What is claimed is:

1. An apparatus comprising:
a gas inter-turbine engine combustor having an annular duct defining a combustor passage extending annularly around a centerline of a gas turbine engine, the centerline of the gas turbine engine parallel to an annular turbine flow path of the gas turbine engine, a working fluid inlet positioned on a radially outward side of the annular duct relative to the centerline of the gas turbine engine, and an outlet positioned on a radially inner side of the combustor passage relative to the centerline of the gas turbine engine, wherein the working fluid inlet is configured to swirl a working fluid as the working fluid passes through the working fluid inlet; and
a fuel injector positioned on a radially outer side of the annular duct relative to the centerline of the gas turbine engine within the working fluid inlet, wherein the fuel injector is angled relative to a radial plane such that a mixture of fuel and working fluid is conveyed to flow circumferentially about the combustor passage from an exit of the fuel injector and toward the outlet, wherein the outlet is in a shape of a tube that radially extends away from the combustor passage and projects into the annular turbine flow path from a wall that at least partially defines the annular turbine flow path, wherein the tube is positioned in the annular turbine fluid flow path upstream from a first row of turbine blades and downstream from a second row of turbine blades.

2. The apparatus of claim 1 , which further includes a cooling space arranged around the gas inter-turbine engine combustor, and wherein the fuel injector is disposed within a circumferential flow path of the working fluid provided via the working fluid inlet.

3. The apparatus of claim 1 , wherein the fuel injector is angled between about 3-4 degrees from the radial plane.

4. The apparatus of claim 1 , wherein the fuel injector is positioned toward a first end of the combustor passage and which further includes an igniter positioned toward a second end of the combustor passage such that a swirling motion of a fuel and working fluid mixture traverses the combustor passage in a circumferential motion for ignition.

5. An apparatus comprising:
a gas turbine engine including a working fluid annulus that defines an annular turbine flow path in which rows of rotatable turbine blades are disposed; and
an inter-turbine combustor having a toroidal construction defining a combustor passage extending annularly around a centerline of the gas turbine engine and that is radially offset from the annular turbine flow path of the gas turbine engine,
the combustor passage including an air inlet disposed on a radially outward side of the toroidal construction relative to the centerline of the gas turbine engine, the combustor passage further including a fuel dispenser coaxial with the air inlet, the fuel dispenser is angled, relative to a radial plane, toward an outlet defined on a radially inward side of the toroidal construction,
wherein the outlet is upstream, relative to the annular turbine flow path, from the air inlet and fuel dispenser and the outlet opens into an elongated member that radially extends from the inter-turbine combustor and through a wall of the working fluid annulus that at least partially defines the annular turbine flow path, wherein the elongated member projects into the annular turbine flow path from the wall and is positioned between the rows of rotatable turbine blades.

6. The apparatus of claim 5 , wherein the toroidal construction extends axially between a first axial side and a second axial side, and wherein the outlet of the combustor passage is disposed toward the first axial side.

7. The apparatus of claim 6 , wherein the fuel dispenser and air inlet are structured to swirl a mixture of fuel and air along a circumferential direction within the combustor passage toward the outlet.

8. The apparatus of claim 7 , wherein the fuel dispenser and air inlet are disposed toward the second axial side, the second axial side located downstream of the first axial side relative to the annular turbine flow path.

9. The apparatus of claim 5 , wherein the fuel dispenser and air inlet provide a fuel rich mixture for combustion within the combustor passage,
and which further includes a tube extending from the outlet, wherein a surface of the tube defines an opening in communication with a central passage of the tube.

10. The apparatus of claim 5 , which further includes a cooling space outside of the inter-turbine combustor that is in fluid flow communication with a turbine vane disposed in the annular turbine flow path downstream of an outlet of the inter-turbine combustor.

11. The apparatus of 10 , wherein the outlet of the inter-turbine combustor is located between a relatively high pressure turbine and a relatively low pressure turbine.

12. An apparatus comprising:
a gas turbine engine having a center line and a working fluid flow path through a compressor, combustor, and turbine having rows of turbine blades;
a combustion passage defined by an annular duct extending annularly around the center line and radially offset from the working fluid flow path and structured to circumferentially flow a mixture of fuel and working fluid around the working fluid flow path, the combustion passage including an igniter for combustion of the mixture of fuel and working fluid and an outlet defined on a radially inner side of the annular duct;
a working fluid inlet positioned on a radially outer side of the annular duct relative to the center line;
a fuel injector coaxial with the working fluid inlet configured to provide fuel for the working fluid, the fuel injector being positioned in the working fluid inlet;
a swirler positioned adjacent the fuel injector such that the working fluid is mixed with fuel from the fuel injector and conveyed from an exit of the swirler and along a circumferential direction about the combustion passage; and
an elongated member in fluid communication with the outlet positioned on the radially inner side of the annular duct, the elongated member projecting into the working fluid flow path from a wall that at least partially defines the working fluid flow path, wherein the elongated member is positioned between the rows of turbine blades.

13. The apparatus of claim 12 , wherein the swirler includes a means for swirling the working fluid around the fuel injector.

14. A method comprising:
operating a gas turbine engine having rows of rotating turbine blades disposed in a working fluid annulus;
circumferentially injecting, relative to a center line of the gas turbine engine, a working fluid and fuel into a first axial side of a combustion passage defined by an annular duct from a working fluid inlet and a fuel injector coaxial with the working fluid inlet, the working fluid inlet and the fuel injector positioned on a radially outer side of the annular duct relative to the center line, and oriented circumferentially relative to the center line, wherein the fuel injector is angled relative to a radial plane;
conveying the circumferentially injected working fluid and fuel in an upstream direction, relative to the working fluid annulus of the gas turbine engine, from an exit of a swirler adjacent to the fuel injector, toward a tubular outlet that extends into the working fluid annulus from a radially inner side of the annular duct at a second axial side of the combustion passage;
combusting a mixture of working fluid and fuel; and
passing a combustion flow through at least a portion of the tubular outlet that projects into the working fluid annulus from a wall that at lea

Assignees

• Chin Jushan
• Rolls Royce Corp

Inventors

• Chin Jushan

Classifications

• F23R3/52

  Toroidal combustion chambers · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23R2900/03341

  Sequential combustion chambers or burners · CPC title

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F23R3/34 Primary

  Feeding into different combustion zones · CPC title