US20090139235A1

US20090139235A1 - Catalytically Stabilized Gas Turbine Combustor

Info

Publication number: US20090139235A1
Application number: US11/949,069
Authority: US
Inventors: Lewis Berkley Davis, Jr.; David Justin Balevic; John Joseph Lipinski
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2007-12-03
Filing date: 2007-12-03
Publication date: 2009-06-04
Also published as: CH698218A2; JP2009139084A; CN101451718A; DE102008037608A1

Abstract

A gas turbine combustor. The gas turbine combustor may include a central combustion nozzle with a catalyst therein and a number of outer combustion nozzles surrounding the central combustion nozzle.

Description

TECHNICAL FIELD

The present application relates generally to gas turbine engines and more particularly relates to a combustor for a gas turbine that is catalytically stabilized.

BACKGROUND OF THE INVENTION

At temperatures above about 2800 degrees Fahrenheit (about 1538 degrees Celsius), the oxygen and nitrogen present in the air combine to form nitrogen oxides (NO and NO₂, collectively known as NO_x.) As a result, modem low emission gas turbines generally use a very lean, premixed flame for low NO_xcombustion. Operational boundaries include “Lean Blow Out” (“LBO”), which may result in a partial or a complete blowout of the flame in one or more combustors. Another boundary is acoustic pressure oscillations or combustion dynamics. These combustion dynamics may influence the operability or durability of the combustion system as a whole. As a result, it may be necessary to tune individually each gas turbine to remain operational while still satisfying emissions controls. Tuning, however, can influence not only the time required for commissioning, but also may be needed to address ambient or load variations.
Both the LBO and combustion dynamics boundaries can be influenced by providing a stable anchoring flame for the combustor. In older low NO_xcombustors, this anchoring flame may be provided by a piloting diffusion flame. This type of pilot, however, may cause NO_xemissions to be higher than desired or permitted. Specifically, the use of a diffusion pilot makes it difficult to reach the desired single digit NO_xemissions in modem gas turbines with high firing temperatures.
Thus, there is a desire for a more stable anchoring flame for low NO_xcombustors. Such a stable anchoring flame should reduce blow out tendency, increased hot section life, relax tuning requirements, and enhance the low NO_xoperating range.

SUMMARY OF THE INVENTION

The present application thus provides a combustor for a gas turbine. The gas turbine combustor may include a central combustion nozzle with a catalyst therein and a number of outer combustion nozzles surrounding the central combustion nozzle.
The present application further provides for operating a gas turbine combustor with a central combustion nozzle and a number of outer combustion nozzles. The method includes the steps of positioning a catalyst within the central combustion nozzle and modulating a fuel-air mixture exiting the central combustion nozzle to a temperature range of about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius).
The present application further provides for a gas turbine combustor. The gas turbine combustor may include a catalytic combustion nozzle with a catalyst therein and a number of non-catalytic combustion nozzles positioned about the catalytic combustion nozzle.
These and other features of the present application will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a side cross-section view of a gas turbine engine showing portions of a combustor, a compressor, and a turbine.

FIG. 2 is a front plan view of a dry low NO_xcombustor as is described herein.

FIG. 3 is a side cross-sectional view of a catalytic combustor as is described herein.

DETAILED DESCRIPTION

Referring now to the drawings, in which like numerals refer to like elements throughout the several views, FIG. 1 shows a portion of a gas turbine engine 100. Generally described, the gas turbine engine 100 includes a compressor 110. The compressor 110 compresses an incoming airflow. The airflow is then discharged to a combustor 120. The combustor 120 includes a number of combustion cans 130. The compressed air and fuel are ignited in the combustion cans 130 and used to drive a turbine section 140. In the turbine section 140, the energy of the hot combustion gases is converted into mechanical work. Some of the work is used to drive the compressor 110 via a shaft 150 with the remainder being available to drive a load such as a generator. By way of example, the gas turbine engine 100 may be a 7FA+e utility gas turbine engine available from General Electric Company of Schenectady, N.Y. Other types of gas turbine engines 100 with a combustor 120 may be used herein.
The combustor 120 may be a dry low NO_x(“DLN”) combustor also available from General Electric Company of Schenectady, N.Y. Specifically, the combustor 120 may be known as a DLN 2.6 combustor. As is shown in FIG. 2, a DLN 2.6 combustor 160 includes a first nozzle 170 and five (5) surrounding outer nozzles, a second nozzle 180, a third nozzle 190, a fourth nozzle 200, a fifth nozzle 210, and a sixth nozzle 220. Any number of nozzles may be used herein. The first nozzle 170 may be fueled separately from the outer nozzles 180-220. The first nozzle 170 therefore may have a separate manifold 175 as compared to the outer nozzles 180-220. The fuel-air ratio of the first nozzle 170 thus can be modulated relative to the outer nozzles 180-220. The outer nozzles 180-200 may be identical with the first nozzle 170 being similar but with a simplified geometry so as to fit within the available space. Emission goals of about nine (9) ppm NO_xand CO over about a fifty percent (50%) load range may be possible. Other types and configurations of combustors 160 may be used herein.
FIG. 3 shows a catalytic combustor 230 as is described herein. The catalytic combustor 230 may be largely identical to the DLN 2.6 combustor 160 described above but with the first nozzle 170 replaced with a catalytic nozzle 240. The catalytic nozzle 240 may include one or more catalyst layers 250 positioned therein. Other configurations of the catalytic combustor 230 and the catalytic nozzle 240 may be used herein.
The catalyst layer 250 may include as an active ingredient precious metals, Group VIII noble metals, base metals, metal oxides, or any combination thereof. Elements such as zirconium, vanadium, chromium, manganese, copper, platinum, palladium, osmium, iridium, rhodium, cerium, lanthanum, other elements of the lanthanide series, cobalt, nickel, iron, and the like may be used. The catalyst layer 250 may be applied directly to a substrate or to an intermediate bond coat or washcoat composed of alumina, silica, zirconia, titania, magnesia, other refractory metal oxides, or any combination thereof. The catalyst-coated substrate may be fabricated from any of various high temperature materials. High temperature metal alloys are preferred, particularly alloys composed of iron, nickel, and/or cobalt, in combination with aluminum, chromium, and/or other alloying materials. High temperature nickel alloys are especially preferred. Other materials that may be used include ceramics, metal oxides, intermetallic materials, carbides, and nitrides. Metallic substrates are most preferred due to their excellent thermal conductivity, allowing effective backside cooling of the catalyst layer 250. Other materials and configurations may be used herein.
The catalytic nozzle 240 may be a nozzle sold under the designation “RCL” by Precision Combustion, Inc. of New Haven, Conn. Other types of catalytic nozzles 240 may be used herein. Only a fraction of the fuel may be reacted such that the internal temperature of the nozzle 240 may be kept within an acceptable range. A mixture of air, unreacted fuel, combustion products, and highly reactive partial combustion products may be injected by the nozzle 240 into a combustion stream. The mixture ideally would be in the temperature range of about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius). When the stream from catalytic nozzle 240 is injected into the swirling mixture of fuel and air provided by the outer nozzles 180-220, this relatively hot, highly reactive gas stream should provide a stable anchor to the premix flame. The outer nozzles 180-220 thus may be modulated to a lower operating temperature.
The relatively low temperature of the partially reacted gases should produced very little NO_xby the pilot flame. The gases from the nozzle 240 are not intended to ignite the mixture within the combustor 230 but only to provide a stable anchor for the flame once ignited. By providing this relatively low temperature anchor, operability may be improved and combustion dynamics reduced without adversely impacting NO_xemissions.
Several or all of the outer nozzles 180-220 also may be replaced with the catalytic nozzle 240. This replacement offers the possibility of obtaining significantly lower NO_xemission levels beyond that achievable by conventional lean premix combustors. Any number or configuration of catalytic nozzles 240 may be used herein.
It should be apparent that the foregoing relates only to the preferred embodiments of the present application and that numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.

Claims

1. A gas turbine combustor, comprising:

a central combustion nozzle;

the central combustion nozzle comprising a catalyst therein; and

a plurality of outer combustion nozzles surrounding the central combustion nozzle.

2. The gas turbine combustor of claim 1, wherein the plurality of outer combustion nozzles comprises five (5) combustion nozzles.

3. The gas turbine combustor of claim 1, wherein the central combustion nozzle comprises a central combustion nozzle manifold.

4. The gas turbine combustor of claim 1, wherein the catalyst comprises precious metals, Group VIII noble metals, base metals, metal oxides, or a combination thereof.

5. The gas turbine combustor of claim 1, wherein the catalyst comprises zirconium, vanadium, chromium, manganese, copper, platinum, palladium, osmium, iridium, rhodium, cerium, lanthanum, other elements of the lanthanide series, cobalt, nickel, or iron.

6. The gas turbine combustor of claim 1, wherein the central combustion nozzle comprises a combustion stream in a temperature range of about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius).

7. The gas turbine combustor of claim 1, wherein one or more of the plurality of outer combustion nozzles comprise a catalyst therein.

8. The gas turbine combustor of claim 1, wherein the catalyst comprises one or more catalyst layers.

9. A method operating a gas turbine combustor with a central combustion nozzle and a plurality of outer combustion nozzles, comprising:

positioning a catalyst within the central combustion nozzle; and

modulating a fuel-air mixture exiting the central combustion nozzle to a temperature range of about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius).

10. The method of claim 9, further comprising modulating a fuel-air mixture exiting the plurality of outer combustion nozzles to a temperature less than about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius).

11. The method of claim 9, further comprising positioning a catalyst within one or more of the outer combustion nozzles.

12. A gas turbine combustor, comprising:

a catalytic combustion nozzle;

the catalytic combustion nozzle comprising a catalyst therein; and

a plurality of non-catalytic combustion nozzles positioned about the catalytic combustion nozzle.

13. The gas turbine combustor of claim 12, wherein the catalytic combustion nozzle comprise a central combustion nozzle and wherein the plurality of non-catalytic combustion nozzles comprise a plurality of non-catalytic nozzles surrounding the central combustion nozzle.

14. The gas turbine combustor of claim 12, wherein the catalytic combustion nozzle comprises a catalytic combustion nozzle manifold.

15. The gas turbine combustor of claim 12, wherein the catalyst comprises precious metals, Group VIII noble metals, base metals, metal oxides, or a combination thereof.

16. The gas turbine combustor of claim 12, wherein the catalyst comprises zirconium, vanadium, chromium, manganese, copper, platinum, palladium, osmium, iridium, rhodium, cerium, lanthanum, other elements of the lanthanide series, cobalt, nickel, or iron.

17. The gas turbine combustor of claim 12, wherein the catalytic combustion nozzle comprises a combustion stream in a temperature range of about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius).

18. The gas turbine combustor of claim 12, further comprises a plurality of catalytic combustion nozzles.

19. The gas turbine combustor of claim 12, wherein the catalyst comprises one or more catalyst layers.