APPARATUS AND METHOD FOR MINIMIZING AND/OR ELIMINATING DILUTION AIR LEAKAGE IN A COMBUSTION LINER ASSEMBLY

Abstract

A combustion liner assembly for a gas turbine includes an outer liner, the outer liner having a flange at a forward end. An inner liner is disposed within the outer liner. The inner liner has a first inner wall. A venturi includes a second inner wall, a venturi throat, and the first inner wall of the inner liner. A slip joint is connected to the second inner wall. The slip joint receives the flange of the outer liner. Alternatively, or additionally, the combustion liner assembly includes a slip joint between the inner or outer liner and an aft section.

Description

The present invention relates to apparatus and methods for minimizing or eliminating dilution air leakage paths in a gas turbine combustor and particularly relates to apparatus and methods for managing dilution air leakage to achieve lower emission levels.

BACKGROUND OF THE INVENTION

Significant products of combustion in gas turbine emissions are oxides of nitrogen, i.e., NO and NO₂ collectively called NO_x, carbon monoxide CO, and unburned hydrocarbons as well as other particulates. Various systems have been proposed and utilized for reducing emissions. For example, water or steam injection into the burning zone of the gas turbine combustor, catalytic clean-up of NO_x and CO from the gas turbine exhaust and dry low NO_x combustors have been used in the past. Compressor discharge dilution air introduced into the liner sleeve of the combustor and transition piece has also been utilized to reduce emissions.

BRIEF DESCRIPTION OF THE INVENTION

According to an embodiment of the invention, a combustion liner assembly for a gas turbine comprises an outer liner, the outer liner having a flange at a forward end; an inner liner disposed within the outer liner, the inner liner having a first inner wall; a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; and a slip joint connected to the second inner wall, the slip joint receiving the flange of the outer liner.

According to another embodiment of the invention, a combustion liner assembly for a gas turbine comprises an outer liner; an inner liner disposed within the outer liner, the inner liner having a first inner wall; a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; an aft section connected to aft ends of the outer liner and the inner liner; and a slip joint provided between the aft section and the inner liner.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic illustration of a gas turbine combustion liner assembly according to an embodiment of the invention;

FIG. 2 is a schematic illustration of a venturi throat of the combustion liner assembly of FIG. 1;

FIG. 3 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention;

FIG. 4 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention;

FIG. 5 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention;

FIG. 6 is a schematic illustration of an aft, or goose neck, section of the combustion liner assembly according to another embodiment of the invention;

FIG. 7 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention;

FIG. 8 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention; and

FIG. 9 is a schematic illustration of a flange of the outer liner and slip joint according to an embodiment of the invention.

DETAILED DESCRIPTION OF THE INVENTION

Referring to FIG. 1, a combustion liner assembly 2 comprises an outer liner 4 and an inner liner 6. A venturi 8 is provided at a forward end of the combustion liner assembly 2 and includes a venturi throat 10 which is provided between the inner liner 6 and an inner wall 12. A flange 14 may be integrally formed with the outer liner 4 and is received in a slip joint 16 that is connected to the inner wall 12 of the venturi 8.

The inner liner 6 includes an inner wall 24 and turbulators 18 provided on an outer surface. An aft section, or gooseneck section, 20 is connected to the aft portion of the outer liner 4 and the inner liner 6. Radial drain or dump holes 22 are provided in the inner liner at an area adjacent to the aft section 20.

The combustion liner assembly 2 may be welded to a liner sleeve at areas A and B corresponding to the slip joint 16 and the end of the aft section 20, respectively. The combustion liner assembly 2 may be circumferentially welded to the liner sleeve, rather than riveted as in prior art arrangements.

Referring to FIG. 2, the venturi 10 may be circumferentially welded to the inner wall 12 and the inner wall 24 of the inner liner 6. The thickness of the inner wall 24 and the thickness of the inner wall 24 of the inner liner 6 at the portion containing the circumferential weld may be thicker than prior art combustion liner assembly inner liners to increase the structural integrity of the venturi, as the venturi will be welded to the liner sleeve as opposed to riveted.

The radial drain or dump holes 22 of the embodiment shown in FIGS. 1 and 2 provides a radial discharge of cooling flow into the flame zone. The embodiments shown in FIGS. 1 and 2 may also have an increased impingement cooling area combined with the turbulators 18. A small controlled leak may be provided into the cooling channel between the outer liner 4 and the inner liner 6 as an alternative to a bellows.

Referring to FIG. 3, according to another embodiment of the invention, the combustion liner assembly 2 includes the aft section, or gooseneck section 20 which comprises axial drain or dump holes 24, rather than radial drain or dump holes. It has been found that the use of radial drain or dump holes, as shown in the embodiment of FIGS. 1 and 2, may trigger high frequency combustion instability, or screech, during transfer to the premix combustion and at the turndown when the flame temperature is reduced. However, the axial drain or dump holes 24 do not trigger high frequency instability with the integral venturi of the embodiment shown in FIG. 3.

As shown in FIGS. 1 and 2, the venturi cooling is rerouted to have an axial discharge with the same effective area as the radial discharge of the venturi of the embodiment shown in FIG. 3.

Referring to FIGS. 4 and 5, a combustion liner assembly 2 according to another embodiment comprises an outer liner 4 and an inner liner 6. The outer liner 4 includes a flange 14 that is received in a slip joint 16 that is connected to an inner wall 12 of a venturi 8 that comprises a venturi throat 10 that connects the inner wall 12 and a portion of the inner liners 6 having axial drain or dump holes 24. At the aft section or, gooseneck section 20, the combustion liner assembly 2 comprises radial drain or dump holes 22 formed in the inner liner 6.

Referring to FIG. 6, according to another embodiment, the dump holes 26 may be provided as holes on the face of the aft section 20, i.e. at the intersection of the cylindrical and conical portions of the aft section 20.

Referring to FIG. 7, a combustion liner assembly according to another embodiment comprises an outer liner 4 and an inner liner 6. A venturi 8 is provided at a forward section of the combustion liner assembly 2 and includes a venturi throat 10 and an inner wall 12. The venturi 8 also includes an inner wall 24 connected between the venturi throat 10 and the inner liner 6. An aft section 20 is connected to the outer liner 4 and the inner liner 6 by an aft slip joint 30. The combustion liner assembly 2 comprises radial drain or dump holes 22 provided in the inner liner 6.

The aft end of the combustion liner assembly 2 comprises a bellows 28, as well as a slip joint 30 as disclosed in the previous embodiments.

Referring to FIG. 8, according to another embodiment of the invention, a combustion liner assembly 2 includes an outer liner 4 and an inner liner 6. A venturi 8 comprises a venturi throat 10 welded to an inner wall 12 and an inner wall 24 connected to the inner liner 6. A flange 14 of the outer liner 4 is received in a slip joint 16 at the forward end of the combustion liner assembly 2. An aft section 20 of the combustion liner 2 is connected to the outer liner 4 and the inner liner 6 by an aft slip joint 30.

Referring to FIG. 9 the slip joint 16 may be formed of, for example, an alloy of primarily nickel, such as Hastelloy®, and the flange 14 may be formed of, for example, stainless steel. The slip joint 16 may also be provided with a wear resistant coating. The slip joint 16 provides a double seal on both sides of the flange 14 and may be machined to tight tolerances. As the temperature of the combustion liner assembly 2 increases during operation of the gas turbine, the small leakage area between the flange 14 and the slip joint 16 decreases as the flange 14 expands into the slip joint 16.

The combustion liner assemblies reduce, or eliminate, airflow losses in between the venturi wall and the liner wall so that airflow can be used and more evenly dispersed. Reduction, or elimination, of variance to air flow will allow more consistent air flow to be utilized in fuel air mixture in the head end combustion zone rather than leak air flow into direct “stream”. The combustion liner assemblies are relatively easy to manufacture and produce a more repeatable air flow from can to can and in turn help to create better fuel air mixture pattern than current design and lower combustion emissions. These are improvements to variation and mixing fuel air better through the mixing holes than would happen through the current design.

The combustion liner assemblies reduce, or eliminate, leaks so airflow in more non-critical areas is conserved and made more consistent, i.e. can to can variation is lowered. The combustion liner assemblies also increase airflow in useable areas in a more dispersed and even mixing through the mixing holes than would happen through current designs.

The combustion liner assemblies can be replaced in the field easily. The existing liners can be pulled out and replaced with the combustion liner assemblies disclosed herein. The combustion liner assemblies may also use current production methods and machining to produce. The combustion liner assemblies do not change the fit, form or function of the overall liner assembly.

While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiments, it is to be understood that the invention is not to be limited to the disclosed embodiments, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims

1. A combustion liner assembly for a gas turbine, comprising:

an outer liner, the outer liner having a flange at a forward end;

an inner liner disposed within the outer liner, the inner liner having a first inner wall;

a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; and

a slip joint connected to the second inner wall, the slip joint receiving the flange of the outer liner.

2. A combustion liner assembly according to claim 1, further comprising an aft section provided at aft ends of the outer liner and the inner liner.

3. A combustion liner assembly according to claim 1, further comprising:

a second slip joint connecting the aft section and the outer liner or the inner liner.

4. A combustion liner assembly according to claim 1, wherein the outer liner comprises a plurality of radial drain or dump holes.

5. A combustion liner assembly according to claim 2, wherein the aft section comprises a plurality of radial drain or dump holes.

6. A combustion liner assembly according to claim 5, wherein the aft section further comprises a plurality of axial drain or dump holes.

7. A combustion liner assembly according to claim 2, wherein the aft section comprises a plurality of axial drain or dump holes.

8. A combustion liner assembly according to claim 2, wherein the aft section comprises a plurality of holes at an intersection of a cylindrical section of the aft section and a conical section of the aft section.

9. A combustion liner assembly according to claim 1, wherein the slip joint is formed of a nickel alloy and the flange is formed of stainless steel.

10. A combustion liner assembly according to claim 1, wherein the slip joint comprises a wear coating.

11. A combustor for a gas turbine, comprising:

a liner sleeve; and

a combustion liner assembly according to claim 1, wherein the combustion liner assembly is welded to the liner sleeve at least at the slip joint.

12. A combustion liner assembly for a gas turbine, comprising:

an outer liner;

an inner liner disposed within the outer liner, the inner liner having a first inner wall;

a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner;

an aft section connected to aft ends of the outer liner and the inner liner; and

a slip joint provided between the aft section and the inner liner.

13. A combustion liner assembly according to claim 12, wherein the aft section further comprises a bellows.

14. A combustion liner assembly according to claim 12, wherein the outer liner comprises a plurality of radial drain or dump holes.

15. A combustion liner assembly according to claim 12, wherein the aft section comprises a plurality of radial drain or dump holes.

16. A combustion liner assembly according to claim 15, wherein the aft section further comprises a plurality of axial drain or dump holes.

17. A combustion liner assembly according to claim 12, wherein the aft section comprises a plurality of axial drain or dump holes.

18. A combustion liner assembly according to claim 12, wherein the aft section comprises a plurality of holes at an intersection of a cylindrical section of the aft section and a conical section of the aft section.

19. A combustion liner assembly according to claim 12, wherein the slip joint comprises a wear coating.

20. A combustor for a gas turbine, comprising:

a liner sleeve; and

a combustion liner assembly according to claim 12, wherein the combustion liner assembly is welded to the liner sleeve.