Patent Application
20160102864
Not applicable.
The present invention relates generally to an apparatus and method for sealing an aft region of a gas turbine combustor. More specifically, the present invention provides an apparatus and method for controlling the amount of compressed air passed to a combustor for cooling and for mixing prior to injection in the combustion liner.
In an effort to reduce the amount of pollution emissions from gas-powered turbines, governmental agencies have enacted numerous regulations requiring reductions in the amount of oxides of nitrogen (NOx) and carbon monoxide (CO). Lower combustion emissions can often be attributed to a more efficient air distribution control process, with specific regard to fuel injector location, airflow rates, and mixing effectiveness.
Early combustion systems utilized diffusion type nozzles, where fuel is mixed with air external to the fuel nozzle by diffusion, proximate the flame zone. Diffusion type nozzles historically produce relatively high emissions due to the fact that the fuel and air burn essentially upon interaction, without mixing, and stoichiometrically at high temperature to maintain adequate combustor stability and low combustion dynamics.
An alternate means of premixing fuel and air and obtaining lower emissions can occur by utilizing multiple combustion stages. In order to provide a combustor with multiple stages of combustion, the fuel and air, which mix and burn to form the hot combustion gases, must also be staged. By controlling the amount of fuel and air passing into the combustion system, available power as well as emissions can be controlled. Fuel can be staged through a series of valves within the fuel system or dedicated fuel circuits to specific fuel injectors. Air, however, can be more difficult to stage given the large quantity of air supplied by the engine compressor.
Of importance to the operation of a combustion system is also regulating the amount of compressed air supplied to the combustion system for mixing and reacting with fuel and as providing a source of cooling air. Therefore, it is necessary to carefully control the distribution of compressed air entering the combustion system. A number of modern day gas turbine combustion systems include a flow sleeve encompassing a combustion liner, where the flow sleeve can at least partially regulate the amount of air entering the combustion system. One such combustion system 100 is shown in
Referring now to
The present invention discloses an apparatus and method for regulating compressed air supply to a combustion system. More specifically, in an embodiment of the present invention, a sealing system for a gas turbine combustor is disclosed. The sealing system comprises a combustion liner located along an axis of a gas turbine combustor and a flow sleeve positioned radially outward of the combustion liner so as to form an annular passage between the combustion liner and the flow sleeve. The sealing system also comprises a compressible seal having a first annular portion, a second annular portion, and a transition portion therebetween. The seal is positioned between the flow sleeve and the combustion liner and includes a plurality of openings for regulating the amount of compressed air that can pass through the seal.
In an alternate embodiment of the present invention, a seal for a gas turbine combustor is disclosed. The seal comprises a first annular portion having a first diameter and a second annular portion having a second diameter, where the second annular portion is radially outward of the first annular portion. The seal also includes a transition portion extending between the first annular portion and the second annular portion, where the transition portion has a plurality of openings for regulating a flow of cooling fluid.
In yet another embodiment of the present invention, a method of regulating cooling fluid flow to a gas turbine combustor is disclosed. More specifically, the method comprises providing a seal extending between a combustion liner and a flow sleeve where the seal has a plurality of slots and a plurality of openings. A cooling fluid is directed across the seal with the seal permitting a predetermined amount of air to enter a passageway located between the combustion liner and the flow sleeve.
Additional advantages and features of the present invention will be set forth in part in a description which follows, and in part will become apparent to those skilled in the art upon examination of the following, or may be learned from practice of the invention. The instant invention will now be described with particular reference to the accompanying drawings.
The present invention is described in detail below with reference to the attached drawing figures, wherein:
The present invention discloses a system and method for regulating the flow of compressed air to a combustion system. The present invention is shown in detail in
The compressible seal 410 serves to regulate airflow passing therethrough for cooling of combustion liner 402 and then into the combustion liner 402 for mixing with fuel. The compressible seal 410 provides a way of regulating the amount of cooling air permitted to pass into the annular passage 408 between the flow sleeve 406 and combustion liner 402. In some prior art combustion systems, as shown in
Referring back to
The annular ring 413 is positioned about the aft end 418 of the combustion liner 402 and forms a cooling channel 420. The cooling channel 420 is supplied with cooling air through one or more feed holes 422. Cooling air passes through the cooling channel 420 and exits the aft end 418 of the combustion liner 402.
As discussed above, and shown in
Referring to
The compressible seal 410 also comprises a transition portion 416 extending between the first annular portion 412 and the second annular portion 414. The transition portion 416 includes a way of regulating airflow passing through the compressible seal 410. More specifically, the transition portion 416 comprises a plurality of openings 428 positioned about the transition portion 416. The plurality of openings 428 can be placed about the transition portion 416 in a variety of ways. Such embodiments include an equal, uniform distribution of openings 428, arranging the openings 428 into a plurality of rows, or a pre-determined pattern of openings 428 to distribute airflow in a pre-determined manner. For example, in an embodiment of the present invention, there are three rows of thirty-six holes in the transition portion 416 along with two rows of holes in the flow sleeve 406, as shown in
Depending on the embodiment of the compressible seal 410, the plurality of axial slots 426 may or may not intersect with the plurality of rows of openings 428. The openings 428 can be placed in the transition portion 416 through a variety of manners such as punching, EDM, or laser cutting of the transition portion 416. As one skilled in the art understands, the diameter of the openings 428 will vary and is a function of the desired mass flow to combustion liner 402, cooling requirements, and cross flow effects in the annular passage 408.
Depending on the exact fit-up of the compressible seal 410 to the flow sleeve inlet ring 424, the effective area that remains open to permit air flow to pass therethrough can vary. For example, in a nominal fit-up embodiment of the present invention, the total amount of flow area open through the seal is about 0.55% of the total area. However, under a looser fit condition, such as either smaller seal diameter or larger inlet ring 424 diameter, the amount of total flow area (leakage) through the compressible seal can approximately double to 1.11%. The compressible seal 410 is sized such that the second annular portion 414 is preferably oversized by up to 0.020 inches in diameter in order to create an interference fit with the flow sleeve inlet ring 424.
The fit-up of the compressible seal 410 also provides a thermally free structural support for the flow sleeve. The compressible seal 410 provides support that is capable of accommodating out of round mating surfaces without inducing constraint due to thermal growth. More specifically, the structural interaction between the compressible seal and the flow sleeve provides acoustical dampening by resisting the acoustical response of the hardware.
The compressible seal 410 can be fabricated from a variety of materials and methods. For example, the compressible seal 410 is generally fabricated from a single sheet of materials that is cut, rolled, welded and the formed to the desire diameter. Acceptable type seal materials include, but are not limited to, Inconel 718 and Hastelloy X, both nickel-based alloys. For the embodiment depicted, the compressible seal 410 has a thickness of approximately 0.060 inches. However, the seal thickness can be changed to vary the amount of preload applied to the seal 410. Alternatively, other materials can be used, although these materials will have slightly less desirable material properties. The material chosen should have some flexibility or spring to it due to the required compression of the axial slots 426.
Referring now to
In operation, the compressed air discharges from an engine compressor and is directed into a plenum in which the one or more combustion liners 402 and flow sleeves 406 are located. The compressed air is then drawn in to the combustion system through the plurality of openings 428 in the transition portion 416. The openings 428 are sized to create a desired pressure drop and may be additionally sized to reduce thermal gradients along a combustion liner due to impingement effects on the liner surface. More specifically, for an embodiment of the present invention, the size of each opening 428 is determined based on its relationship with the liner 402. The annulus of each opening 428 is projected onto the surface of the liner 402 with respect to the opening centerline. The downstream surface area of this projection forms the general area available for the flow to exit opening 428. In order to minimize the flow variation due to manufacturing tolerances or misalignment of the liner with respect to the flow sleeve, and ultimately ensure the opening 428 controls the flow, this projection area is approximately 2.5 times the area of each opening 428.
As discussed above, a portion of the compressed air is drawn downstream towards the aft end 418 of the combustion liner 402, into the passageway 420 where it serves to cool the combustion liner aft end 418. However, a majority of the compressed air is directed upstream towards an inlet of the combustion liner 402. This compressed air is directed between the flow sleeve 406 and the combustion liner 402, through the annular passage 408. The compressed air cools the wall of the combustion liner 402 as the air passes upstream towards the inlet end. To aid in enhancing the cooling effectiveness of the compressed air, the combustion liner 402 may also include a plurality of heat transfer devices commonly referred to as trip strips. The heat transfer devices comprise a plurality of raised edges in the combustion liner wall, the raised edges extending into the flow of compressed air, so as to cause the flow to trip, thereby enhancing the heat transfer effectiveness of the compressed air.
In order to minimize the wear on the flow sleeve inlet ring 424 and the compressed seal 410, the second annular portion 414 of the compressible seal 410 and the inner diameter region of the flow sleeve inlet ring 424 can each have a wear reduction coating applied, such as a hardface coating. Therefore, any wear occurs to the coatings and not the components themselves.
An alternate embodiment of the present invention is shown in
The sealing system 1000 also comprises a transition duct 1008 having a first wall 1010 and a second wall 1012 located radially outward of the first wall 1010. The transition duct 1008 engages the combustion liner 1002, where the aft end of the combustion liner 1002 is slidably engaged in the first wall 1010 of the transition duct 1008. The sealing system 1000 also comprises a compressible seal 1014 having a first annular portion 1016 and a second annular portion 1018. The compressible seal 1014 is secured to the flow sleeve 1004 along the first annular portion 1016. The means by which the compressible seal 1014 is secured can include welding or brazing. For welding, the compressible seal 1014 can be welded by resistance spot welds spaced about the perimeter of the seal, manual TIG welding, or other similar welding techniques.
As shown in
Referring now to
As shown in
The plurality of holes 1022 and axial slots 1024 provide a way of directing cooling fluid, such as compressed air, to the passageway 1006. The holes 1022 are sized so as to supply a majority of the cooling fluid to the passageway 1006. However, the plurality of axial slots 1024 can also provide some cooling fluid depending on their final size when the flow sleeve 1004 is secured to the second wall 1012 of the transition duct 1008.
Alternatively, the compressible seal 1014 may be oriented in an opposing direction, as shown in
While the invention has been described in what is known as presently the preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment but, on the contrary, is intended to cover various modifications and equivalent arrangements within the scope of the following claims. The present invention has been described in relation to particular embodiments, which are intended in all respects to be illustrative rather than restrictive.
From the foregoing, it will be seen that this invention is one well adapted to attain all the ends and objects set forth above, together with other advantages which are obvious and inherent to the system and method. It will be understood that certain features and sub-combinations are of utility and may be employed without reference to other features and sub-combinations. This is contemplated by and within the scope of the claims.
