Combustion chamber for a gas turbine

Abstract

A combustion chamber (100) for a gas turbine includes a combustion chamber (102) having an inlet (104). The combustion chamber inlet (104) is defined by a burner (30). The burner includes: an ignition burner section (200) centered on a central axis (Y); a swirler section (300) including stationary blades (302) extending radially outward from the ignition burner section (200); and a main burner section (400) extending radially outward from and surrounding the swirler section (300).

Description

Technical Field

[0001] This disclosure relates to a combustion chamber for a gas turbine and a method for operating the combustion chamber for a gas turbine. Background Technology

[0002] In such technological fields, a typical objective is to reduce emissions, particularly high emissions of nitrogen oxides (NOx) caused by the high temperatures inside the combustion chamber. Specifically, the mixing of fuel and gas (air) inside the combustion chamber is considered a key issue in avoiding areas with high temperatures and thus reducing total NOx emissions.

[0003] Typically, a combustion chamber includes a main combustion chamber and a pre-combustion chamber located upstream of the main combustion chamber. The pre-combustion chamber includes a swirler section with swirlers through which air and fuel can be supplied.

[0004] The ignition fuel is typically injected further by an ignition burner in a direction roughly parallel to the central axis of the combustion chamber. The ignition fuel is used to control the combustion chamber flame in which the main fuel burns.

[0005] Hydrogen is gaining popularity as a fuel for generating electricity in gas turbines. Most gas turbine systems that can burn a high percentage of hydrogen are diffusion-based. Due to minimal or no premixing, the injected fuel burns at a high equivalence ratio, resulting in very high local temperatures and consequently high NOx emissions.

[0006] Most combustion systems in current natural gas combustion systems use dry low-emission (DLE) technology, in which fuel and air are premixed to reduce NOx emissions.

[0007] The desire is for systems that can use hydrogen, natural gas, or a mixture of both as fuel. However, constructing a system operable using both natural gas and hydrogen that produces low NOx emissions and minimizes the risk of combustion (“backfire”) in the premixed region is challenging. Summary of the Invention

[0008] The purpose of this disclosure may be to provide a combustion chamber that provides low nitrogen oxide (NOx) emissions.

[0009] Another object of this disclosure is to provide a combustion chamber having a desired fuel distribution in a mixture of gases inside the combustion chamber.

[0010] Another object of this disclosure may be to provide a combustion chamber having a desired flame profile.

[0011] This objective is achieved by a combustion chamber for a gas turbine according to the present disclosure. This disclosure describes advantageous improvements and modifications thereof.

[0012] According to this disclosure, an apparatus as set forth in the appended claims is provided. Other features of this disclosure will become apparent from the dependent claims and the following description.

[0013] Therefore, a combustion chamber (100) for a gas turbine can be provided, which extends along a central axis (Y) and includes a combustion chamber (102) having an inlet (104). A burner (30) is disposed in, configured, and / or defines the inlet (104). The combustion chamber inlet (104) (i.e., the burner 30) may include an ignition burner section (200) centered on the central axis (Y), and the ignition burner section defines a fuel delivery conduit (202) having an inlet (204) for fluid communication with a fuel source.

[0014] The ignition burner section (200) may also include a fuel injector (206) in fluid communication with the fuel delivery conduit (202). The burner (30) may also include: a swirler section (300) including stationary blades (302) extending radially outward from the ignition burner section (200); and a main burner section (400) extending radially outward from and surrounding the swirler section (300).

[0015] The ignition burner section (200) is spaced apart from the main burner section (400) to define an annular swirling flow path (320) extending between the ignition burner section (200) and the main burner section (400), the annular swirling flow path (320) including an upstream plane (722) and an outlet plane (726).

[0016] The main burner section (400) may define a plurality of premixed flow passages (402), each of which extends from a premixed flow passage inlet (404) on the inlet face (406) of the main burner section (400) to a premixed flow passage outlet (408) on the outlet face (410) of the main burner section (400).

[0017] The main burner section (400) may also include a fuel manifold (412), each of the premixed flow passages (402) being provided with a fuel injector (414) in flow communication with the fuel manifold (412). The fuel manifold (412) may be in communication with the fuel delivery conduit (202) in the ignition burner section (200) via a fuel flow passage (304) extending through the swirler section (300).

[0018] The annular swirling flow path (320) can be between the upstream plane (722) and the outlet plane (726) and diverge in the direction from the upstream plane (722) toward the outlet plane (726).

[0019] The annular swirling flow path (320) may have a central path line (728) at the outlet plane (722), the central path line (728) may have an angle Ɵ relative to the central axis Y of the combustion chamber (100). The angle Ɵ may be ≥ 5° and ≤ 45°, preferably, the angle Ɵ may be between ≥ 10° and ≤ 25°.

[0020] The combustion chamber (100) may include an outlet face (410) facing downstream or toward the combustion chamber (102). The outlet face (410) includes a central region (730) defining a radially inward region of the outlet face (410) starting from a central path line (728) at the outlet plane (726). The central region (730) has a radius R1, and the outlet face (410) has a radius R2. The radius R1 may be between 25% and 75% of R2 and includes both 25% and 75% of R2, preferably, R1 may be between 40% and 50% of R2 and includes both 40% and 50% of R2, and preferably, R1 may be 50% of the radius R2.

[0021] The cross-sectional area of ​​the outlet plane (726) may be the same as or smaller than the cross-sectional area of ​​the upstream plane (722) of the annular swirling flow path (320). Preferably, the cross-sectional area of ​​the outlet plane (726) is at most 10% smaller than and includes 10% of the cross-sectional area of ​​the upstream plane (722).

[0022] Each stationary blade (302) may have a leading edge (303) and a trailing edge (306). The downstream direction (Y1) may be defined by a direction from the leading edge (303) of the stationary blade along the central axis (Y) to the trailing edge (306) of the stationary blade. The upstream direction (Y2) may be defined by a direction from the trailing edge (306) of the stationary blade along the central axis (Y) to the leading edge (303) of the stationary blade.

[0023] The stationary blades (302) may be spaced apart from each other around the outer periphery of the ignition burner section (200) to define oxidant flow passages (308), each oxidant flow passage (308) having a flow inlet (310) at the leading edge (303) of the stationary blade and a flow outlet (312) at the trailing edge (306) of the stationary blade.

[0024] The ignition burner section (200) can extend axially in the upstream direction (Y2) away from the leading edge (303) of the stationary blade, and in the downstream direction (Y1) away from the trailing edge (306) of the stationary blade.

[0025] The fuel injector (206) of the ignition burner section (200) is located downstream of the trailing edge (306) of the stationary blade.

[0026] Combustion chamber 102 can be defined upstream by outlet face 410, allowing fuel / air injection to directly enter the "main" combustion chamber 102. For example, outlet face 410 of the main burner section 400 defines (i.e., provides) at least a portion of the boundary / limitation of the combustion zone of combustion chamber 102. With this arrangement, combustion does not occur upstream of outlet face 410 of the main burner section 400.

[0027] The premixed flow passage inlet (404) may have a first shape on the inlet face (406) of the main burner section (400), and the premixed flow passage outlet (408) may have a second shape on the outlet face (410) of the main burner section (400). The cross-sectional shape of the premixed flow passage (402) may change from the first shape to the second shape along the length of the premixed flow passage (402).

[0028] The first shape can be a polygonal shape selected from a list including squares, rectangles, and hexagons; and the second shape can be a circle.

[0029] The premixed flow path (402) can be grouped into rows (420) that extend radially away from the central axis (Y), wherein the radial extension path (416) of the manifold (412) extends between the rows (420).

[0030] The cross-sectional area of ​​the premixed flow path inlet (404) can increase with the distance from the central axis (Y).

[0031] The fuel manifold (412) of the main burner section (400) may also include a manifold pressurization chamber (422) which is arranged in series between the fuel flow passage (304) of the cyclone section (300) and each radial extension passage (416) of the manifold (412).

[0032] The manifold pressurization chamber (422) can be divided into sub-pressurization chambers by the support column (440).

[0033] The main burner section (400) may also include a cooling pressurization chamber (430) adjacent to the outlet surface (410) of the main burner section (400).

[0034] The cooling booster chamber (430) may have an inlet (432) located on the outer periphery of the main burner section (400) and at least one outlet (434) located between the rows (420) of the premixed flow passage outlet (408) on the outlet surface (410) of the main burner section (400).

[0035] Some fuel injectors (414) in the premixed flow path (402) may be configured to be a first distance X1 away from the inlet surface (406) of the main burner section (400); and other (e.g., the rest) fuel injectors (414) in the premixed flow path (402) may be configured to be a second distance X2 away from the inlet surface (406) of the main burner section (400) that is greater than the first distance X1.

[0036] The fuel injectors (414) located in the radially inner premixed flow passage (402) and the radially outer premixed flow passage (402) can be positioned at a first distance X1 from the inlet surface (406) of the main burner section (400). The fuel injectors (414) located in the premixed flow passage (402) between the radially inner premixed flow passage (402) and the radially outer premixed flow passage (402) can be positioned at a second distance X2 from the inlet surface (406) of the main burner section (400).

[0037] The outlet face (410) of the main burner section (400) may extend orthogonally relative to the central axis (Y). The outlet face (410) of the main burner section (400) may extend at an angle relative to the central axis (Y), such that the radially outer premixed flow passage outlet (408) is located downstream of the radially inner premixed flow passage outlet (408).

[0038] The main burner section (400) may extend axially away from the trailing edge (306) of the stationary blade in the downstream direction (Y1); the ignition burner section (200) is spaced apart from the main burner section (400) to define an annular swirling flow path (320) extending from the trailing edge (306) of the stationary blade between the ignition burner section (200) and the main burner section (400).

[0039] The diameter of the annular swirling flow path (320) can increase as the distance from the trailing edge (306) of the stationary blade increases in the downstream direction (Y1).

[0040] The distance between the main burner section (400) and the ignition burner section (200) can decrease as the distance from the trailing edge (306) of the stationary blade increases in the downstream direction (Y1), so that the flow area of ​​the annular swirling flow path (320) decreases as the distance from the trailing edge (306) of the stationary blade increases in the downstream direction (Y1).

[0041] The ignition burner section (200) may define an oxidant flow passage (208) that extends from an oxidant flow passage inlet (220) located on an inlet face (222) of the ignition burner section (200) to an ignition burner oxidant flow passage outlet (226) located on an outlet face (224) of the ignition burner section (200); the inlet face (222) is located upstream of the outlet face (224); and the outlet face (224) is located downstream of the fuel injector (206) of the ignition burner section (200).

[0042] The oxidizer flow passage outlet (226) of the igniter burner may include multiple orifices (228), which lead to the outlet surface (224) of the igniter burner section (200); the oxidizer flow pressurization chamber (230) of the igniter burner may be located between the oxidizer flow passage (208) and the multiple orifices (228), and may be in flow communication with the oxidizer flow passage (208) and the multiple orifices (228).

[0043] The first flow guide cap (431) can extend from the radial outer surface (433) of the main burner section (400) in the upstream direction (Y2) away from the inlet surface (406) of the main burner section (400); and the second flow guide cap (435) can extend from the radial inner surface (424) of the main burner section (400) in the upstream direction (Y2) away from the inlet surface (406) of the main burner section (400), thereby defining the main burner section inlet flow path (436) between the first flow guide cap (431) and the second flow guide cap (435); and thereby defining the swirler section inlet flow path (336) between the second flow guide cap (435) and the radial outer surface (232) of the ignition burner section (200).

[0044] The combustion chamber can be an annular combustion chamber or a canister combustion chamber. The combustion chamber can have a cylindrical or elliptical shape. The combustion chamber may include a main combustion chamber.

[0045] Advantageously, compared to examples of the prior art, the above features of this disclosure provide improved mixing of the oxidizer / fuel mixture before it enters the combustion chamber, thereby reducing NOx emissions, regardless of whether the fuel is hydrogen, natural gas, or a mixture of both. Attached Figure Description

[0046] Examples of this disclosure will now be described with reference to the accompanying drawings, in which:

[0047] Figure 1 A longitudinal cross-sectional view of a gas turbine engine including a combustion chamber according to the present disclosure is shown;

[0048] Figure 2 A partial longitudinal section of a combustion chamber for a gas turbine according to this disclosure is shown;

[0049] Figure 3 It shows Figure 2 The diagram shows a partial longitudinal equidistant cross-sectional view of the combustion chamber.

[0050] Figure 4 It shows Figure 2 , Figure 3 An enlarged view of a portion of the combustion chamber burner shown;

[0051] Figure 5 It shows Figure 2 , Figure 3 and Figure 4 A diagram showing the flow path;

[0052] Figure 6 Shown from different angles Figure 4 The view;

[0053] Figure 7 It shows Figure 2 , Figure 3 An enlarged view of a portion of the combustion chamber burner shown;

[0054] Figure 8 It shows Figure 2 , Figure 3 The isometric cross-sectional view of the combustion chamber burner shown is illustrated; and

[0055] Figure 9 , Figure 10 Similar to Figure 7 The view shows another example of the area of ​​the combustion chamber burner. Detailed Implementation

[0056] The details presented in the accompanying drawings are for illustrative purposes only. Similar or identical elements are given the same reference numerals in different drawings.

[0057] Figure 1 An example of a gas turbine engine 10 is shown in cross-section. The gas turbine engine 10 includes, in flow sequence, an inlet 12, a compressor section 14, a combustion chamber section 16, and a turbine section 18, which are generally arranged in flow sequence and generally about and along a longitudinal axis or rotation axis 20. The gas turbine engine 10 also includes a shaft 22, which is rotatable about the rotation axis 20 and extends longitudinally through the gas turbine engine 10. The shaft 22 drivesly connects the turbine section 18 to the compressor section 14.

[0058] During the operation of the gas turbine engine 10, the air 24 drawn in through the air inlet 12 is compressed by the compressor section 14 and delivered to the combustion section (or burner section) 16.

[0059] Combustion section 16 includes a combustor pressurization chamber 108 and one or more combustion chambers 102. Combustion section 16 also includes at least one burner 30 defining an inlet 104 for each combustion chamber 102. As described below, each burner at the inlet 104 includes an ignition burner section 200, a swirler section 300, and a main burner section 400. Compressed air passing through compressor 14 enters diffuser 32 and is discharged from diffuser 32 into combustor pressurization chamber 108. A portion of the air from combustor pressurization chamber 108 enters ignition burner section 200, swirler section 300, and main burner section 400 and mixes with gaseous or liquid ignition fuel in ignition burner section 200 and swirler section 300. The air / fuel mixture then combusts, and the combustion gases 34 or working gases produced by combustion are directed through combustion chamber 102 to turbine section 18 via transition pipe 17.

[0060] The main stream of the air / fuel mixture is further inserted into the ignition burner section 200 via fuel conduit 202, as described in more detail below. The main fuel, after exiting the burner 30 at inlet 104, is burned while mixing with the hot gas in chamber 102.

[0061] The exemplary gas turbine engine 10 has an annular combustion chamber section 16, which is composed of an annular array of combustion chamber canisters 19, each of which has a burner 30 and a combustion chamber 102. A transition duct 17 has a generally circular inlet that engages with the combustion chamber 102 and an outlet in the form of an annular segment. The outlet of the annular array of transition ducts forms an annular element for guiding combustion gases to the turbine 18.

[0062] The turbine section 18 includes a plurality of moving blade support discs 36 attached to the shaft 22. In this example, two discs 36 each support a ring array of turbine moving blades 38. However, the number of moving blade support discs can be different, i.e., there may be only one disc or more than two discs. In addition, guide vanes 40 fixed to the stator 42 of the gas turbine engine 10 are provided between the turbine moving blades 38 of each ring array. An inlet guide vane 44 is provided between the outlet of the combustion chamber 102 and the preceding turbine moving blades 38, and the inlet guide vane 44 directs the working gas flow onto the turbine moving blades 38.

[0063] Combustion gas from combustion chamber 102 enters turbine section 18 and drives turbine moving blades 38, which in turn rotate shaft 22. Guide stationary blades 40 and 44 are used to optimize the angle of combustion gas or working gas on turbine moving blades 38.

[0064] Turbine section 18 drives compressor section 14. Compressor section 14 includes an axially arranged series of stationary blade stages 46 and rotor moving blade stages 48. Rotor moving blade stages 48 include a rotor disk supporting the annular array of moving blades. Compressor section 14 also includes a housing 50 surrounding the rotor stages and supporting the stationary blade stages 46. Guide stationary blade stages include radially extending stationary blades of an annular array mounted to housing 50. The stationary blades are configured to provide gas flow at an optimal angle to the moving blades at a given engine operating point. Some of the guide stationary blade stages have variable stationary blades, wherein the angle of the stationary blades about their own longitudinal axis can be adjusted according to the angle of airflow characteristics that may occur under different engine operating conditions.

[0065] The housing 50 defines the radial outer surface 52 of the passage 56 of the compressor 14. The radial inner surface 54 of the passage 56 is defined at least partially by the rotor drum 53 of the rotor, which is partially defined by the moving blades 48 of the annular array.

[0066] The present disclosure is described with reference to the exemplary turbine engine described above, which has a single shaft or spool connecting a single multi-stage compressor and a single first-stage or more turbines. However, it should be understood that the present disclosure is equally applicable to dual-shaft or triple-shaft engines, and that the present disclosure can be used for industrial, aerospace, or marine applications.

[0067] Unless otherwise specified, the terms upstream and downstream refer to the direction of airflow and / or working gas flow through the engine. When no different designation is made, the terms axial, radial, and circumferential are made with reference to the engine's axis of rotation 20.

[0068] Figure 2 , Figure 3 It shows that it is suitable for use in Figure 1 The combustion chamber 100 used in a gas turbine. The combustion chamber 100 extends along a central axis Y and includes a combustion chamber 102 having an inlet 104. A combustion chamber housing 106 is also provided, which defines (i.e. surrounds) and is spaced apart from the combustion chamber 102 to define a combustor pressurization chamber 108 between the combustion chamber housing 106 and the combustion chamber 102, in use, where an oxidizing gas (e.g., air) is introduced into the combustor pressurization chamber 108 by... Figure 2 , Figure 3The flow is indicated by the arrow in the diagram. The combustion chamber 102 itself and the housing 106 can be conventional and therefore will not be described in more detail.

[0069] The combustion chamber inlet 104 is defined by (i.e. includes) the burner 30, which includes an ignition burner section 200, a swirler section 300, and a main burner section 400. The ignition burner section 200, the swirler section 300, and the main burner section 400 are concentric and / or coaxial, and each is centered on the central axis Y.

[0070] The ignition burner section 200 is centered on the central axis Y. The ignition burner section 200 defines a fuel delivery conduit 202 having an inlet 204 for fluid communication with a fuel source, such as a fuel supply for an engine including hydrogen, natural gas, or a mixture of both. The ignition burner section 200 also includes a fuel injector 206 in fluid communication with the fuel delivery conduit 202.

[0071] The cyclone section 300 includes stationary blades 302 extending radially outward from the ignition burner section 200.

[0072] Each stationary blade 302 has a leading edge 303 and a trailing edge 306. In the context of the apparatus disclosed herein and as such... Figure 2 As shown in the figure, the downstream direction Y1 is defined by the direction from the leading edge 303 of the stationary blade along the central axis Y to the trailing edge 306 of the stationary blade, and the upstream direction Y2 is defined by the direction from the trailing edge 306 of the stationary blade along the central axis Y to the leading edge 303 of the stationary blade.

[0073] Stationary blades 302 are spaced apart from each other around the outer periphery of the ignition burner section 200 to define oxidant flow passages 308. Each oxidant flow passage 308 has a flow inlet 310 located at the leading edge 303 of the stationary blade and a flow outlet 312 located at the trailing edge 306 of the stationary blade. The stationary blades 302 are configured (i.e., sized, angled, shaped, and / or spaced apart) to induce swirl in the fluid (e.g., air) passing through the swirler section 300. Therefore, the flow exiting the flow outlet 312 will (to some extent) be induced to have a circumferential component around the central axis Y.

[0074] like Figure 2 , Figure 3 As illustrated, the main burner section 400 can extend axially in the downstream direction Y1 away from the trailing edge 306 of the stationary blade. The ignition burner section 200 is spaced apart from the main burner section 400 to define an annular swirling flow path 320 extending from the trailing edge 306 of the stationary blade between the ignition burner section 200 and the main burner section 400.

[0075] The diameter of the annular swirling flow path 320 increases with the distance from the trailing edge 306 of the stationary blade along the downstream direction Y1. Therefore, for example... Figure 6 As shown, the wall thickness of the main burner 400 on its inner circumference decreases with increasing distance from the trailing edge 306 of the stationary blade in the downstream direction Y1. Therefore, the diameter of the outer surface of the ignition burner section 200 increases with increasing distance from the trailing edge 306 of the stationary blade in the downstream direction Y1, and the inner circumference of the main burner section 400 increases with increasing distance from the trailing edge 306 of the stationary blade in the downstream direction Y1. In other words, the outer surface of the ignition burner section 200 and the inner circumference of the main burner section 400 expand radially outward with increasing distance from the trailing edge 306 of the stationary blade in the downstream direction Y1. This arrangement allows the main burner to be cooled by the flow traveling along the annular flow path 320, particularly towards and in the region of the outlet surface 410 of the main burner section 400.

[0076] The distance between the main burner section 400 and the ignition burner section 200 decreases as the distance from the trailing edge 306 of the stationary blade increases in the downstream direction Y1, causing the flow area of ​​the annular swirling flow path 320 to decrease as the distance from the trailing edge 306 of the stationary blade increases in the downstream direction Y1. This reduces the pressure of the fluid passing through the swirling flow path 320, thereby continuously accelerating the flow and thus increasing the velocity at the outlet of the flow path 320, and thus reducing the risk of backfire into the flow path 320.

[0077] The ignition burner section 200 extends axially in the upstream direction Y2 away from the leading edge 303 of the stationary blade, and extends axially in the downstream direction Y1 away from the trailing edge 306 of the stationary blade.

[0078] The fuel injector 206 of the ignition burner section 200 is located downstream of the trailing edge 306 of the stationary blade, on the outer surface of the ignition burner section 200, and within the annular swirling flow path 320. Therefore, the flow exiting the flow outlet 312 passes through the outlet of the fuel injector 206 of the ignition burner section 200, resulting in fuel leaving the injector mixing with air. Multiple fuel injectors 206 of the ignition burner section 200 can be arranged around the circumference of the ignition burner section 200, each fuel injector 206 operable to inject fuel into the turbulent flow exiting the flow path outlet 312.

[0079] The fuel injector 206 in this position reduces the time available for premixing before entering the combustion chamber 102 (i.e., the combustion zone), and therefore, a cavity will be present in the combustion chamber 102 (i.e., in the combustion zone) for a fuel / air mixture that will have a higher fuel:air ratio compared to other fuel / air mixtures. Consequently, these cavities will be "fuel-rich," providing a stable ignition flame during engine start-up, acceleration, and low-load turbine load operation.

[0080] The main burner section 400 extends radially outward from the cyclone section 300 and surrounds (i.e. defines) the cyclone section 300.

[0081] like Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 7 , Figure 9 and Figure 10 As shown, the main burner section 400 defines a plurality of premixed flow passages 402, each of which extends from a premixed flow passage inlet 404 located on the inlet face 406 of the main burner section 400 to a premixed flow passage outlet 408 located on the outlet face 410 of the main burner section 400.

[0082] Therefore, as Figure 2 , Figure 3 As shown, the combustion chamber 102 (and therefore the combustion zone) can be defined upstream by the outlet face 410 of the main burner section 400. Therefore, fuel / air is injected directly into the combustion chamber 102. Thus, the outlet face 410 of the main burner section 400 defines (i.e. provides) at least a portion of the boundary / boundary of the combustion zone of the combustion chamber 102. With this arrangement, combustion does not occur upstream of the outlet face 410 of the main burner section 400, but only downstream of the outlet face 410 of the main burner section 400.

[0083] For example, as a cross-sectional view through burner 30 Figure 8 As shown in the view, the main combustor section 400 also includes (i.e., defines) a fuel manifold 412, and each premixed flow passage in the premixed flow passage 402 is provided with a fuel injector 414 in flow communication with the fuel manifold 412.

[0084] The fuel manifold 412 is connected to the fuel delivery conduit 202 in the ignition burner section 200 via a fuel flow passage 304 extending through the cyclone section 300.

[0085] The premixed flow passage inlet 404 has a first shape on the inlet surface 406 of the main burner section 400, and the premixed flow passage outlet 408 has a second shape on the outlet surface 410 of the main burner section 400. The cross-sectional shape of the premixed flow passage 402 changes from the first shape to the second shape along the length of the premixed flow passage 402.

[0086] Although it has rounded corners, the first shape can be a polygonal shape selected from a list including squares, rectangles, and hexagons, and the second shape can be a circle.

[0087] The shape variation along the length of the premixed flow path 402 will generate turbulence for better mixing of fuel and air, resulting in lower NOx formation. A gradual transition to a circular shape will reduce the risk of backfire.

[0088] A circular outlet 408 is preferred because it forms a flow jet with the flow pattern desired for combustion. However, having a polygonal shape at the inlet 404 means that the inlet size can be optimized for the amount of space available on the inlet face 406, since polygonal, and especially square and rectangular, inlets can be arranged with the minimum area of ​​the burner face 406 that obstructs the flow of oxidizer.

[0089] The cross-sectional area of ​​each premixed flow path inlet 404 can be reduced along its length from inlet face 406 to outlet face 410. The cross-sectional area of ​​each premixed flow path inlet 404 can be reduced by no more than 30% along its length from inlet face 406 to outlet face 410. The cross-sectional area of ​​each premixed flow path inlet 404 can be reduced by at least 5% but no more than 20% along its length from inlet face 406 to outlet face 410. This slight reduction in area enhances premixing. The reduction in area also increases the flow velocity of the jet exiting outlet 408. This promotes jet formation, which is important for reducing backfire, especially for fuels containing a large amount of hydrogen.

[0090] This arrangement also results in less variation in the fuel:air ratio between the premixed flow paths 402. Therefore, this will also reduce the variation in the stoichiometric ratio between the premixed flow paths 402. The stoichiometric ratio is defined as the ratio of the actual fuel:air ratio to the stoichiometric fuel:air ratio.

[0091] like Figure 4 , Figure 5 , Figure 6 , Figure 8 , Figure 9 and Figure 10 As illustrated, the premixed flow passage 402 can be grouped into rows 420 extending radially away from the central axis Y, wherein radially extending passages 416 of the manifold 412 extend between rows 420. Figure 8 The example in the diagram shows three premixed flow paths 402 located in each radially extending row. Figure 4 , Figure 5 The example shown illustrates six premixed flow paths 402 located in each radially extending row. In other examples, a single loop of premixed flow paths 402 may be present. In other examples, two or more premixed flow paths 402 may be present in each radially extending row 420.

[0092] like Figure 5 , Figure 8 As illustrated, the cross-sectional area of ​​the premixed flow path inlet 404 increases with increasing distance from the central axis Y. Figure 5 As best illustrated, the cross-sectional shape of the premixed flow passage inlet 404 can change with increasing distance from the central axis Y. For example, it is square in the radially inner section of the row 420 and changes to a rectangle as the distance from the central axis Y increases in the radially outer direction.

[0093] like Figure 8 As shown, the fuel manifold 412 of the main combustor section 400 may also include a manifold pressurization chamber 422, which is arranged in series between the flow passage 304 of the cyclone section 300 and each radial extension passage 416 of the manifold 412.

[0094] The manifold booster chamber 422 is divided into sub-booster chambers by the strut 440. This can be configured to stage the fuel in the circumferential direction by dividing the fuel into four to six different zones. The number of stationary vanes needs to be changed accordingly. For example, for four zones, eight stationary vanes can be used, such that two stationary vanes are accommodated at each 90-degree angle and the sectors of the pipe cover 90 degrees.

[0095] like Figure 6 As illustrated, the main burner section 400 may further include a cooling pressurization chamber 430 adjacent to the outlet surface 410 of the main burner section 400. The cooling pressurization chamber 430 may have an inlet 432 located on the outer periphery of the main burner section 400 and at least one outlet 434 located on the outlet surface 410 of the main burner section 400 between rows 420 of the premixed flow passage outlet 408. Multiple inlets 432, pressurization chambers 430, and outlets 434 may be provided, for example, one inlet, pressurization chamber, and outlet may be provided between each pair of rows 420 of the premixed flow passage 402.

[0096] like Figure 7As illustrated, some fuel injectors 414 in the premixed flow passage 402 can be configured to be a first distance X1 away from the inlet surface 406 of the main burner section 400, and some fuel injectors 414 in the premixed flow passage 402 can be configured to be a second distance X2 away from the inlet surface 406 of the main burner section 400, the second distance X2 being greater than the first distance X1.

[0097] In one example not shown, fuel injectors 414 located in the radially inner premixed flow passage 402 and the radially outer premixed flow passage 402 are positioned at a first distance X1 from the inlet surface 406 of the main burner section 400, and fuel injectors 414 located in the premixed flow passage 402 between the radially inner premixed flow passage 402 and the radially outer premixed flow passage 402 are positioned at a second distance X2 from the inlet surface 406 of the main burner section 400.

[0098] X1 can be in the range of 5% to 30% of the length of the premixed flow path 402, and X2 can be in the range of 15% to 50% of the length of the premixed flow path 402.

[0099] The amount of premixing will vary depending on the location of the fuel injector 414 in different examples of premixed flow paths within the premixed flow path 402. Therefore, there will be more premixing where the fuel injector 414 is closer to the inlet face 406 than where it is closer to the outlet face 410. This can improve combustion dynamics because a fuel:air ratio gradient will exist at the outlet of the main combustor 400.

[0100] Figure 7 Details of an example of annular swirling flow path 320 are shown. The annular swirling flow path 320 is located between an upstream plane 722 and an outlet plane 726 and diverges in a direction from the upstream plane 722 and the outlet plane 726 or in a downstream direction relative to the flow passing through the outlet plane 726. The outlet plane 726 may be defined by an outlet surface 410. The annular swirling flow path 320 has a central path line 728. At the outlet plane 726, the central path line 728 has an angle Ɵ relative to the central axis Y of the combustion chamber 100. Line Y' is shown and is parallel to the central axis Y. The angle Ɵ may be ≥ 5° and ≤ 45°. Preferably, the angle Ɵ may be between ≥ 10° and ≤ 25°. The diverging annular swirling flow path 320 results in the formation of a recirculation zone of the fuel / air mixture positioned closely around the central axis Y. The recirculation zone increases the residence time for enhanced complete combustion of the fuel-air mixture.

[0101] The divergent annular swirling flow path 320 creates a central region 730 at the outlet face 410 compared to a non-divergent annular swirling flow path 320. The increased central region 730 at the outlet face 410 provides a larger flame-holding surface and thus improves flame stability. The central region 730 has a radius R1, and the outlet face has a radius R2. R1 is preferably 50% of R2, but can be between 25% and 75% of R2, and includes both 25% and 75%. Preferably, R1 can be between 40% and 50% of R2, and includes both 40% and 50% of R2. Therefore, the relative size or radius of the central region 730 to the outlet face 410 provides a centrally sized region to allow for flame-holding characteristics. A portion of this swirling flow mixes with fuel and air from the main combustor section 400 downstream of the face 410. The intensity of the fuel-air mixture in flow path 320 can be easily controlled by changing the fuel flow rate, and this allows for control of the combustion zone to reduce emissions, and in particular minimizes nitrogen oxides and carbon monoxide over the gas turbine load range.

[0102] The cross-sectional area of ​​the outlet plane 726 is the same as the cross-sectional area of ​​the upstream plane 722. Therefore, when in Figure 7 When observed, the radial dimension of the annular swirling flow path 320 decreases between upstream planes 722 and along the direction from and to upstream planes 722. In one example, the cross-sectional area of ​​the outlet plane 726 is at most 10% smaller than and includes 10% of the cross-sectional area of ​​the upstream plane 722. Therefore, the fuel-air mixture traveling through the annular swirling flow path 320 is accelerated due to the reduced cross-sectional area of ​​the annular swirling flow path 320. Thus, when using highly reactive fuels, such as fuels containing ≥ 5% hydrogen or high hydrocarbons, the reduced cross-sectional area of ​​the annular swirling flow path 320 provides resistance to potential backfire.

[0103] like Figure 2 , Figure 3 As illustrated, the outlet surface 410 of the main burner section 400 can extend orthogonally relative to the central axis Y. Figure 9 , Figure 10 In an alternative example, the outlet surface 410 of the main burner section 400 extends at an angle of A degrees relative to the central axis Y of the combustion chamber 100, such that the radially outer premixed flow passage outlet 408 is located downstream of the radially inner premixed flow passage outlet 408.

[0104] Therefore, in some examples and such Figure 2 , Figure 3 As illustrated, angle A can be 90 degrees relative to the combustion chamber axis Y. In other examples, such as... Figure 9 , Figure 10 As shown, angle A can be less than 90 degrees but greater than or equal to 60 degrees relative to the combustion chamber axis Y. For example, angle A can be about 60 degrees relative to the combustion chamber axis Y. When angle A is within this range (i.e., less than 90 degrees and at least 60 degrees), this can promote higher or lower interaction between the gases exiting the ignition section 200 and the main section 400 of the burner 30. In the example where a richer mixture and / or combustion heat products from the ignition section 200 mix with the stream from the main section 400, higher / greater flame stability and / or enhanced blowout limits of the main section 400 can be produced. In other words, Figure 9 , Figure 10 Examples of these technologies can reduce emissions and / or improve combustion dynamics compared to examples of related technologies.

[0105] like Figure 2 , Figure 3 As shown, the ignition burner section 200 defines an oxidizer flow passage 208 that extends from an oxidizer flow passage inlet 220 located on an inlet face 222 of the ignition burner section 200 to an ignition burner oxidizer flow passage outlet 226 located on an outlet face 224 of the ignition burner section 200. The inlet face 222 is located upstream of the outlet face 224. The outlet face 224 is located downstream of the fuel injector 206 of the ignition burner section 200. The outlet face 224 may extend orthogonally relative to the central axis Y.

[0106] The oxidizer flow passage outlet 226 of the igniter burner may include a plurality of orifices 228 leading to the outlet surface 224 of the igniter burner section 200. An oxidizer flow pressurization chamber 230 of the igniter burner may be positioned between the oxidizer flow passage 208 and the plurality of orifices 228, and the oxidizer flow pressurization chamber 230 of the igniter burner may be in flow communication with the oxidizer flow passage 208 and the plurality of orifices 228.

[0107] A first flow guide cap 431 can extend from the radially outer surface 433 of the main burner section 400 along the upstream direction Y2 away from the inlet surface 406 of the main burner section 400. A second flow guide cap 435 can extend from the radially inner surface 424 of the main burner section 400 along the upstream direction Y2 away from the inlet surface 406 of the main burner section 400, thereby defining a main burner section inlet flow path 436 between the first flow guide cap 431 and the second flow guide cap 435, and thereby defining a swirler section inlet flow path 336 between the second flow guide cap 435 and the radially outer surface 232 of the ignition burner section 200. Figure 2 , Figure 3 , Figure 6 , Figure 7As shown, the second flow guide cap 435 can open radially away from the inlet surface 406 of the main burner section 400 in the upstream direction Y2 to form a funnel-shaped arrangement for guiding the flow onto the stationary blades 302.

[0108] The combination of flow guide caps 431 and 435 will result in a more uniform distribution of air entering each premixed flow passage 402, so that the fuel:air ratio of the stream leaving the main combustor 400 has a uniform and predictable pattern.

[0109] The device disclosed herein provides a central swirl-stabilized igniter with a larger flame retainer surface compared to related art devices, which will improve turbine operation during startup, acceleration, and under low load. The swirl-stabilized igniter will also enable the engine to respond to varying load demands.

[0110] The nested (i.e. concentric) arrangement of the main burner section 400, the swirl section 300, and the ignition burner 200 provides a distributed flame with multiple shear zones in the radial direction during operation. This configuration provides improved mixing of the oxidizer / fuel mixture before it enters the combustion chamber, thus reducing local peak temperatures and consequently reducing NOx emissions, regardless of whether the fuel is hydrogen, natural gas, or a mixture of both.

[0111] The nested (i.e. concentric) arrangement also ensures that most of the combustion occurs near the inlet 104 of the combustion chamber 100, and thus reduces the volume of carbon monoxide produced compared to examples of related technologies, in the case where natural gas constitutes the fuel composition.

[0112] During operation, the burner 30, which defines the inlet 104, will be heated by the combustion event. The flow through the premixed flow passage 402 will absorb heat from the burner, and since all the fuel and air passing through the premixed flow passage 402 will be heated to a similar degree, the combustion characteristics of the fuel / air mixture caused by heating will be substantially uniform.

[0113] During operation, compared to conventional swirl-stabilized burners, this arrangement of the ignition burner 200 and the main burner 400 results in a more uniform heat release from combustion in a direction orthogonal to the Y-axis (i.e., radially outward from the Y-axis). Therefore, the temperature distribution at the turbine inlet will be more uniform compared to burners of related technologies, leading to an increased lifespan for the turbine section.

[0114] In particular, the higher number of fuel injection points and the increased premixed distributed fuel-air arrangement provide lower NOx emissions.

[0115] The configuration of the device disclosed herein also provides greater backfire resistance without requiring any restrictions in the premixed flow path 402, which allows for a higher mass flow rate through the premixed flow path 402.

[0116] The configuration disclosed herein is advantageous because it is easily scalable by changing the number of premixed flow passages 402 and the diameter of the burner section while maintaining a similar structure.

[0117] Please note all papers and documents submitted concurrently with or prior to this specification in connection with this application, and these papers and documents are publicly available together with this specification, and the contents of all such papers and documents are incorporated herein by reference.

[0118] All features disclosed in this specification (including any appended claims, abstract, and drawings) and / or all steps of any method or process disclosed thereby may be combined in any combination except for combinations in which at least some of such features and / or steps are mutually exclusive.

[0119] Each feature disclosed in this specification (including any appended claims, abstract, and drawings) may be replaced by an alternative feature for the same, equivalent, or similar purpose, unless otherwise expressly stated. Therefore, unless otherwise expressly stated, each disclosed feature is merely one example of an equivalent or similar feature in a general series.

[0120] This invention is not limited to the details of the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification (including any appended claims, abstract, and drawings), or to any novel step or any novel combination of steps in any method or process disclosed herein.

Claims

1. A combustion chamber (100) for a gas turbine, the combustion chamber (100) extending along a central axis (Y) and including a combustion chamber (102) having an inlet (104); the inlet (104) of the combustion chamber is defined by a burner (30), the burner (30) comprising: Ignition burner section (200), the ignition burner section (200) being centered on the central axis (Y), and the ignition burner section (200) defining a fuel delivery conduit (202) having an inlet (204) for fluid communication with a fuel source and a fuel injector (206) in fluid communication with the fuel delivery conduit (202). The cyclone section (300) includes stationary blades (302) extending radially outward from the ignition burner section (200). The main burner section (400) extends radially outward from the swirler section (300) and surrounds the swirler section (300). The ignition burner section (200) is spaced apart from the main burner section (400) to define an annular swirling flow path (320) extending between the ignition burner section (200) and the main burner section (400), the annular swirling flow path (320) including an upstream plane (722) and an outlet plane (726). The main burner section (400) defines a plurality of premixed flow passages (402), each of which extends from a premixed flow passage inlet (404) located on the inlet face (406) of the main burner section (400) to a premixed flow passage outlet (408) located on the outlet face (410) of the main burner section (400). The main burner section (400) also includes a fuel manifold (412), and each premixed flow passage (402) is provided with a fuel injector (414) in flow communication with the fuel manifold (412). The fuel manifold (412) is in flow communication with the fuel delivery conduit (202) in the ignition burner section (200) via a fuel flow passage (304) extending through the cyclone section (300). The premixed flow passages (402) are grouped into rows (420) extending radially away from the central axis (Y), and the radially extending passages (416) of the fuel manifold (412) extend between the rows (420). In some of the premixed flow passages (402), the fuel injectors (414) are arranged to be a first distance X1 away from the inlet surface (406) of the main burner section (400), and the fuel injectors (414) in other premixed flow passages (402) are arranged to be a second distance X2 away from the inlet surface (406) of the main burner section (400) that is greater than the first distance X1. The fuel injectors (414) in the radially inner and radially outer premixed flow passages (402) are configured to be spaced from the inlet surface (406) of the main burner section (400) by a first distance X1; and The fuel injector (414) in the premixed flow passage (402) located between the radially inner premixed flow passage (402) and the radially outer premixed flow passage (402) is disposed at the second distance X2 from the inlet surface (406) of the main burner section (400).

2. The combustion chamber (100) according to claim 1, wherein, The annular swirling flow path (320) is between the upstream plane (722) and the outlet plane (726) and diverges in a direction from the upstream plane (722) toward the outlet plane (726).

3. The combustion chamber (100) according to claim 2, wherein, The annular swirling flow path (320) has an intermediate path line (728). At the outlet plane (726), the intermediate path line (728) has an angle Ɵ relative to the central axis (Y) of the combustion chamber (100). The angle Ɵ is ≥ 5° and ≤ 45°.

4. The combustion chamber (100) according to claim 3, wherein, The combustion chamber (100) includes an outlet surface (410) that faces downstream or toward the combustion chamber (102). The exit surface (410) includes a central region (730), which is defined as the radially inward region of the exit surface (410) starting from the intermediate path line (728) at the exit plane (726). The central region (730) has a radius R1, and the exit surface (410) has a radius R2. The radius R1 is between 25% and 75% of the radius R2 and includes both 25% and 75% of the radius R2.

5. The combustion chamber (100) according to any one of claims 1 to 4, wherein, The cross-sectional area of ​​the outlet plane (726) is the same as or smaller than the cross-sectional area of ​​the upstream plane (722) of the annular swirling flow path (320).

6. The combustion chamber (100) according to any one of claims 1 to 4, wherein, Each stationary blade (302) has a leading edge (303) and a trailing edge (306); The downstream direction (Y1) is defined by the direction from the leading edge (303) of the stationary blade along the central axis (Y) to the trailing edge (306) of the stationary blade; and the upstream direction (Y2) is defined by the direction from the trailing edge (306) of the stationary blade along the central axis (Y) to the leading edge (303) of the stationary blade. The stationary blades (302) are spaced apart from each other around the outer periphery of the ignition burner section (200) to define oxidant flow passages (308), each oxidant flow passage (308) having a flow inlet (310) at the leading edge (303) of the stationary blade and a flow outlet (312) at the trailing edge (306) of the stationary blade. The ignition burner section (200) extends axially away from the leading edge (303) of the stationary blade in the upstream direction (Y2) and extends axially away from the trailing edge (306) of the stationary blade in the downstream direction (Y1); and The fuel injector (206) of the ignition burner section (200) is located downstream of the trailing edge (306) of the stationary blade.

7. The combustion chamber (100) according to any one of claims 1 to 4, wherein, The premixed flow passage inlet (404) has a first shape on the inlet surface (406) of the main burner section (400), and the premixed flow passage outlet (408) has a second shape on the outlet surface (410) of the main burner section (400); and the cross-sectional shape of the premixed flow passage (402) changes from the first shape to the second shape along the length of the premixed flow passage (402).

8. The combustion chamber (100) according to claim 7, wherein, The first shape is a polygonal shape selected from a list including squares, rectangles, and hexagons; and the second shape is a circle.

9. The combustion chamber (100) according to claim 1, wherein, The cross-sectional area of ​​the premixed flow passage inlet (404) increases with the distance from the central axis (Y).

10. The combustion chamber (100) according to claim 1, wherein, The fuel manifold (412) of the main burner section (400) further includes a manifold pressurization chamber (422), which is arranged in series between the flow passage (304) of the cyclone section (300) and each radial extension passage (416) of the fuel manifold (412).

11. The combustion chamber (100) according to claim 1, wherein, The main burner section (400) further includes a cooling pressurization chamber (430) adjacent to the outlet surface (410) of the main burner section (400); the cooling pressurization chamber (430) has an inlet (432) located on the outer periphery of the main burner section (400) and at least one outlet (434) located on the outlet surface (410) of the main burner section (400) between the rows (420) of the premixed flow passage outlet (408).

12. The combustion chamber (100) according to any one of claims 1 to 4, wherein, The outlet surface (410) of the main burner section (400) extends orthogonally to the central axis (Y); or The outlet surface (410) of the main burner section (400) extends at an angle relative to the central axis (Y), such that the radially outer premixed flow passage outlet (408) is located downstream of the radially inner premixed flow passage outlet (408).

13. The combustion chamber (100) according to claim 6, wherein, The main burner section (400) extends axially away from the trailing edge (306) of the stationary blade in the downstream direction (Y1); The ignition burner section (200) is spaced apart from the main burner section (400) to define an annular swirling flow path (320) extending from the trailing edge (306) of the stationary blade between the ignition burner section (200) and the main burner section (400).

14. The combustion chamber (100) according to claim 6, wherein, The diameter of the annular swirling flow path (320) increases with the distance from the trailing edge (306) of the stationary blade along the downstream direction (Y1).

15. The combustion chamber (100) according to claim 6, wherein, The distance between the main burner section (400) and the ignition burner section (200) decreases as the distance from the trailing edge (306) of the stationary blade increases along the downstream direction (Y1), so that the flow area of ​​the annular swirling flow path (320) decreases as the distance from the trailing edge (306) of the stationary blade increases along the downstream direction (Y1).

16. The combustion chamber (100) according to any one of claims 1 to 4, wherein, The ignition burner section (200) defines an oxidant flow path (208) extending from an oxidant flow path inlet (220) located on the inlet face (222) of the ignition burner section (200) to an ignition burner oxidant flow path outlet (226) located on the outlet face (224) of the ignition burner section (200); the inlet face (222) of the ignition burner section (200) is upstream of the outlet face (224) of the ignition burner section (200); and the outlet face (224) of the ignition burner section (200) is downstream of the fuel injector (206) of the ignition burner section (200).

17. The combustion chamber (100) according to claim 16, wherein, The oxidizer flow passage outlet (226) of the igniter burner includes a plurality of orifices (228), which lead to the outlet surface (224) of the igniter burner section (200); an igniter burner oxidizer flow pressurization chamber (230) is positioned between the oxidizer flow passage (208) and the plurality of orifices (228), and the igniter burner oxidizer flow pressurization chamber (230) is in flow communication with the oxidizer flow passage (208) and the plurality of orifices (228).

18. The combustion chamber (100) according to claim 6, wherein, A first flow guide cap (431) extends from the radial outer surface (433) of the main burner section (400) along the upstream direction (Y2) away from the inlet surface (406) of the main burner section (400), and The second flow guide cap (435) extends from the radial inner surface (424) of the main burner section (400) along the upstream direction (Y2) away from the inlet surface (406) of the main burner section (400); This defines the main burner section inlet flow path (436) between the first flow guide cap (431) and the second flow guide cap (435); and This defines a swirler section inlet flow path (336) between the second flow guide cap (435) and the radial outer surface (232) of the ignition burner section (200).

19. The combustion chamber (100) according to claim 3, wherein, The angle Ɵ is between ≥ 10° and ≤ 25°.

20. The combustion chamber (100) according to claim 4, wherein, The radius R1 is between 40% and 50% of the radius R2 and includes both 40% and 50% of the radius R2.

21. The combustion chamber (100) according to claim 20, wherein, The radius R1 is 50% of the radius R2.

22. The combustion chamber (100) according to claim 5, wherein, The cross-sectional area of ​​the outlet plane (726) is at most 10% smaller than and includes 10% of the cross-sectional area of ​​the upstream plane (722).

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