EP2748443B1

EP2748443B1 - Method of mixing combustion reactants for combustion in a gas turbine engine

Info

Publication number: EP2748443B1
Application number: EP11871108.4A
Authority: EP
Inventors: Majed Toqan; Brent Allan Gregory; Jonathan David Regele; Ryan Sadao Yamane
Original assignee: Individual
Current assignee: Individual
Priority date: 2011-08-22
Filing date: 2011-08-22
Publication date: 2019-04-24
Anticipated expiration: 2031-08-22
Also published as: RU2014110631A; JP6086371B2; EP2748443A4; EP2748443A1; WO2013028169A1; JP2014526030A; CN104053883B; WO2013028169A8; PL2748443T3; CN104053883A; KR101774094B1; KR20140082659A; RU2619673C2

Description

This disclosure relates to devices in gas turbine engines that aid in containing and producing the combustion of a fuel and air mixture. Such devices include but are not limited to fuel-air nozzles, combustor liners and casings and flow transition pieces that are used in military and commercial aircraft, power generation, and other gas turbine related applications.
Gas turbine engines include machinery that extracts work from combustion gases flowing at very high temperatures, pressures and velocity. The extracted work can be used to drive a generator for power generation or for providing the required thrust for an aircraft. A typical gas turbine engine consists of a multistage compressor where the atmospheric air is compressed to high pressures. The compressed air is then mixed at a specified fuel/air ratio in a combustor wherein its temperature is increased.
The high temperature and pressure combustion gases are then expanded through a turbine to extract work so as to provide the required thrust or drive a generator depending on the application. The turbine includes at least a single stage with each stage consisting of a row of blades and a row of vanes. The blades are circumferentially distributed on a rotating hub with the height of each blade covering the hot gas flow path. Each stage of non-rotating vanes is placed circumferentially, which also extends across the hot gas flow path. The included invention involves the combustor of gas turbine engines and components that introduce the fuel and air into the said device.
The combustor portion of a gas turbine engine can be of several different types: can/tubular, annular, and a combination of the two forming a can-annular combustor. It is in this component that the compressed fuel-air mixture passes through fuel-air swirlers and a combustion reaction of the mixture takes place, creating a hot gas flow causing it to drop in density and accelerate downstream. The can type combustor typically comprises of individual, circumferentially spaced cans that contain the flame of each nozzle separately. Flow from each can is then directed through a duct and combined in an annular transition piece before it enters the first stage vane. In the annular combustor type, fuel-air nozzles are typically distributed circumferentially and introduce the mixture into a single annular chamber where combustion takes place. Flow simply exits the downstream end of the annulus into the first stage turbine, without the need for a transition piece to combine the flow. The key difference of the last type, a can-annular combustor, is that it has individual cans encompassed by an annular casing that contains the air being fed into each can. Each variation has its benefits and disadvantages, depending on the application.
In combustors for gas turbines, it is typical for the fuel-air nozzle to introduce a swirl to the mixture for several reasons. One is to enhance mixing and thus combustion, another reason is that adding swirl stabilizes the flame to prevent flame blowout and it allows for leaner fuel-air mixtures for reduced emissions. A fuel air nozzle can take on different configurations such as single to multiple annular inlets with swirling vanes on each one.
As with other gas turbine components, implementation of cooling methods to prevent melting of the combustor material is needed. A typical method for cooling the combustor is effusion cooling, implemented by surrounding the combustion liner with an additional, offset liner, which between the two, compressor discharge air passes through and enters the hot gas flow path through dilution holes and cooling passages.
This technique removes heat from the component as well as forms a thin boundary layer film of cool air between the liner and the combusting gases, preventing heat transfer to the liner. The dilution holes serve two purposes depending on its axial position on the liner: a dilution hole closer to the fuel-air nozzles will aid in the mixing of the gases to enhance combustion as well as provide unburned air for combustion, second, a hole that is placed closer to the turbine will cool the hot gas flow and can be designed to manipulate the combustor outlet temperature profile.
One can see that several methods and technologies can be incorporated into the design of combustors for gas turbine engines to improve combustion and lower emissions. While gas turbines tend to produce less pollution than other power generation methods, there is still room for improvement in this area. With government regulation of emissions tightening in several countries, the technology will need to improve to meet these requirements.
US 2007/0107437 A1 describes a combustor. The combustor includes a combustor liner and a swirl premixer disposed on a head end of the combustor liner and configured to provide a fuel-air mixture to the combustor. The combustor also includes a plurality of tangentially staged injectors disposed downstream of the swirl premixer on the combustor liner, wherein each of the plurality of injectors is configured to introduce the fuel-air mixture in a transverse direction to a longitudinal axis of the combustor and to sequentially ignite the fuel-air mixtures from adjacent tangential injectors.
EP 1 882 885 A2 describes a combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween. An air fuel mixer and an igniter are mounted to the support assembly secured to the ceramic combustion can which receives the ignition products of the ignited fuel and air mixture.
With regard to present invention, there is provided a method of mixing combustion reactants for combustion in a gas turbine engine, according to claim 1. This method provides a novel and improved combustor design that is capable of operating in a typical fashion while minimizing the pollutant emissions that are a result of combustion of a fuel and air mixture and address other issues faced by such devices. The combustor consists of a typical can-annular combustor with premixed fuel-air nozzles and dilution holes that introduce the compressor discharge air and pressurized fuel into the combustor at various locations in the longitudinal and circumferential directions. The original feature of the invention is that the fuel and air nozzles are placed in such a way as to create an environment with enhanced mixing of combustion reactants and products. Staging the premixed fuel and air nozzles to have more fuel upstream from another set of nozzles enhances the mixing of the combustion reactants and creates a specific oxygen concentration in the combustion region that greatly reduces the production of NOx. In addition, the introduction of compressor discharge air downstream of the combustion region allows for any CO produced during combustion to be burned/consumed before entering the first stage turbine. In effect, the combustor will improve gas turbine emission levels, thus reducing the need for emission control devices as well as minimize the environmental impact of such devices. In addition to this improvement, the tangentially firing fuel and fuel-air nozzles directs its flames to the adjacent burner nozzles in each can, greatly enhancing the ignition process of the combustor.

Referring to the drawings:

FIG. 1 is a two-dimensional sketch showing the can-annular arrangement with the nozzles that attach to the outer can liner injecting fuel and air into a common plane;
FIG. 2 is a two-dimensional sketch showing the general idea of the tangential nozzles applied to the can in a can-annular combustor;
FIG. 3 is an isometric side view of the upstream portion of an example configuration of the can;
FIG. 4A is an isometric cutaway view of the can; FIG. 4B is a close up view of the image from FIG. 4A;
FIG. 5 is a section view showing section A-A as defined in FIG. 3; and
FIG. 6 is a section view showing section B-B as defined in FIG. 3.

FIG. 1 shows an example of the general arrangement of a can-annular combustor with the can 1 spaced circumferentially on a common radius, all cans of which are enclosed in an annular space between a cylindrical outer liner 2 and a cylindrical inner liner 3. The figure also shows the tangential nozzle arrangement of the cans. FIG. 2 shows the can in more detail. A can liner 4 forms the can volume, with fuel-air nozzles 5 injecting a premixed fuel and air mixture. The nozzles form an angle 8 between the nozzle centerline 6 and a line tangent to the can liner 4 that intersections with the nozzle centerline 6. This angle defines the circumferential direction of the nozzles.
FIG. 2 also shows the general operation of the can in the example can-annular combustor configuration, where a pre-mixed fuel-air mixture 9 is injected into the cans 1 at an angle 8. A flame 10 forms and travels through the can in a path 11 that follows the can liner. These tangentially directed nozzles result in flames from each nozzle interacting with the downstream and adjacent nozzle. This key feature enhances ignition and reduces the need of piloting burner nozzles by allowing the flame from a nozzle to ignite the fuel at the adjacent and downstream nozzle.
FIG. 3 shows the beginning or upstream portion of an example can with the downstream portion excluded. The can has a plurality of nozzle rows that are spaced along the longitudinal direction of the can. Each row of nozzles has a plurality of nozzles and can be offset by a circumferential angle from adjacent nozzle rows. The can may also have several rows of circumferentially spaced holes 12 or passages for cooling air to enter the can.
FIGS. 4A and 4B show the most upstream face 13 of the can, which has dilution holes 14 that allow compressor discharge air to enter the can.
FIGS. 5 and 6 show how nozzles from each set of rows may be offset by a circumferential angle. The different rows of nozzles allow for the injection of the fuel air mixture near the front wall, which has a higher fuel/air ratio than the second set of nozzles in conjunction with the mixture that is injected downstream of the fuel nozzles 5, to create the desired mixing and fuel-air staging effect that will create an optimal combustion environment that reduces NOx and CO emissions from the combustor.

Claims

A method of mixing combustion reactants for combustion in a gas turbine engine comprising the steps of:
providing a can annular combustor, the can annular combustor including a plurality of circumferentially spaced cans (1) enclosed between two cylindrical liners (2,3), the cans (1) defining separate combustion zones and each can being a can liner, the can liner having an upstream end, including a front wall (13), and a downstream end, the combustion zone being a can volume of the can liner, the can volume extending in a longitudinal direction from the front wall (13) of the upstream end of the can liner to the downstream end of the can liner, a plurality of dilution holes (14) through the front wall (13), first nozzles through the can liner, second nozzles through the can liner, the first nozzles being spaced apart and arranged circumferentially around the combustion zone between the front wall (13) and the downstream end of the can liner, the second nozzles being spaced apart and are arranged circumferentially around the combustion zone between the front wall (13) and the first nozzles, the first nozzles being downstream of the second nozzles toward the downstream end of the can liner and residing in a first plane (B) that is normal to the longitudinal direction of the can volume, and the second nozzles being upstream of the first nozzles toward the upstream end of the can liner and residing in a second plane (A) that is normal to the longitudinal direction of the can volume;

and for each of the cans (1) concurrently:
a) injecting a first premixed fuel-air mixture into the can volume through all of the first nozzles, the first nozzles each applying the first premixed fuel-air mixture into the annular volume in a direction that is angularly offset from a tangent line relative to the can liner;

b) injecting a second premixed fuel-air mixture into the can volume through all of the second nozzles, the second nozzles each applying the second premixed fuel-air mixture into the can volume in a direction that is angularly offset from the tangent line relative to the can liner;
the first premixed fuel-air mixture having a first fuel-air ratio, the second premixed fuel-air mixture having a second fuel air ratio, and the second fuel/air ratio being greater than the first fuel/air ratio; and

c) injecting compressor discharge air through the plurality of dilution holes (14) through the front wall (13) into the can volume in the longitudinal direction of the can volume;
wherein the concurrent steps of injecting the first pre-mixed fuel-air mixture into the can volume through all of the first nozzles, injecting the second premixed fuel-air mixture into the can volume through all of the second nozzles, and injecting compressor discharge air through the plurality of dilution holes (14) through the front wall (13) into the can volume create fuel-air staging for enhancing combustion and reducing NOx and CO emissions.
The method as claimed in claim 1, further comprising the steps of providing circumferentially spaced cooling air holes (12) through the can liner between the downstream end of the can liner and the first nozzles, and circumferentially applying cooling air through the circumferentially spaced cooling air holes (12) into the can volume between the downstream end of the can volume and the first nozzles, for each of the cans (1).
The method as claimed in claim 1, wherein each of the first nozzles direct any flame to an adjacent first nozzle for enhancing combustion, and each of the second nozzles direct any flame to an adjacent second nozzle for enhancing combustion.
The method as claimed in claim 1, wherein the first nozzles are circumferentially offset relative to the second nozzles.