Combustion chamber in a gas turbine engine
By introducing a premixer, auxiliary fuel injector, and collar structure into the combustion chamber, fuel injection and cooling airflow are optimized, solving the problems of unburned emissions and high-temperature efficiency in gas turbine engines, improving combustion efficiency and cooling effect, and extending equipment life.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SIEMENS ENERGY GLOBAL GMBH & CO KG
- Filing Date
- 2021-08-02
- Publication Date
- 2026-07-24
AI Technical Summary
Gas turbine engines suffer from unburned hydrocarbon emissions and efficiency issues at high temperatures, and it is necessary to ensure complete combustion within the combustion chamber.
Introducing premixed fuel injectors and auxiliary fuel injectors into the combustion chamber, combined with a collar structure, forms upstream and downstream purging paths to optimize fuel injection and cooling air flow, thereby improving combustion efficiency and cooling effect.
It improves combustion efficiency in the combustion chamber, reduces unburned emissions, extends the design life of the gas turbine engine, optimizes the use of cooling air, and enhances overall performance.
Smart Images
Figure CN117795253B_ABST
Abstract
Description
Background Technology
[0001] A gas turbine engine typically includes a compressor section, a turbine section, and a combustion section located between the compressor section and the turbine section. The compressor section includes multi-stage rotating compressor blades and stationary compressor vanes. The combustion section typically includes multiple combustion chambers. The turbine section includes multi-stage rotating turbine blades and stationary turbine vanes.
[0002] The combustion chamber may include a fuel injector for supplying fuel to be mixed with compressed air from the compressor section and an ignition source for igniting the mixture to form hot exhaust gases for the turbine section. Gas turbine combustion may produce undesirable emissions, including unburned hydrocarbons. Additionally, operation at higher temperatures results in higher efficiency. Therefore, it is desirable to operate at the highest possible temperature and to ensure complete combustion within the combustion chamber. Summary of the Invention
[0003] In one aspect, the combustion chamber includes a premixed fuel injector that injects fuel into the combustion chamber and ignites a mixture of fuel and compressed air to produce exhaust gas. The combustion chamber includes an internal transition duct defining the passage of the exhaust gas. The transition duct defines an opening through which the transition duct passes. The opening has an upstream side and a downstream side defined by the flow direction of the exhaust gas. The combustion chamber includes an auxiliary fuel injector disposed in the opening that injects further fuel into the exhaust gas. The combustion chamber includes a collar fixedly coupled to the transition duct and positioned around the auxiliary fuel injector. The collar has a first end positioned to the outside of the transition duct, a second end fixed to the transition duct around the opening, and a wall located between the first end and the second end. The collar cooperates with the auxiliary fuel injector to define an upstream purge path at least partially disposed on the upstream side and a downstream purge path at least partially disposed on the downstream side, each providing flow communication between the outside and the inside of the transition duct. The upstream purge path has a larger flow area compared to the downstream purge path.
[0004] In one aspect, a combustion chamber includes an internal transition duct defining the flow of combustion gases through which a flow passes in the flow direction. The transition duct defines an opening through which it passes. The opening has an upstream side and a downstream side defined by the flow direction. The combustion chamber includes an auxiliary fuel injector at least partially disposed within the opening to inject fuel into the flow of combustion gases. The combustion chamber includes a collar fixedly coupled to the transition duct and positioned around the opening. The collar cooperates with the auxiliary fuel injector to define an upstream purge path at least partially disposed on the upstream side of the opening and a downstream purge path at least partially disposed on the downstream side of the opening, the upstream and downstream purge paths each providing flow communication between the exterior and interior of the transition duct. The upstream purge path has a larger flow area than the downstream purge path.
[0005] In one aspect, a combustion chamber includes an internal transition conduit through which a flow of combustion gases passes in a flow direction. The transition conduit defines an opening through which it passes. The opening has an upstream side and a downstream side defined by the flow direction. The combustion chamber includes an auxiliary fuel injector at least partially disposed within the opening to inject fuel into the flow of combustion gases. The combustion chamber includes a collar fixedly coupled to the transition conduit and positioned around the opening. The collar cooperates with the auxiliary fuel injector to define an upstream purge path at least partially disposed on the upstream side of the opening and a downstream purge path at least partially disposed on the downstream side of the opening, the upstream and downstream purge paths each providing flow communication between the exterior and interior of the transition conduit. The upstream purge path has a larger flow area than the downstream purge path. The collar includes a plurality of upstream orifices facing the upstream side of the opening and a plurality of downstream orifices facing the downstream side of the opening. The plurality of upstream orifices define the upstream purge path, and the plurality of downstream orifices define the downstream purge path. Each of the plurality of upstream orifices is larger in size than each of the plurality of downstream orifices. The total number of upstream orifices is greater than the total number of downstream orifices. The upstream purging path has a larger circumferential length around the periphery of the collar compared to the downstream purging path. The upstream and downstream purging paths are separated by two ribs located on the inner surface of the collar. Attached Figure Description
[0006] To facilitate identification of any discussion of a particular element or action, one or more of the highest-order digits in the reference numerals indicate the drawing number in which the element was first introduced.
[0007] Figure 1 It is a longitudinal cross-sectional view of a gas turbine engine taken along a plane containing the longitudinal axis or central axis.
[0008] Figure 2 The diagram shows Figure 1 A longitudinal cross-sectional view of the combustion section of a gas turbine engine.
[0009] Figure 3 The diagram illustrates what is suitable for use in Figure 2 A three-dimensional view of the combustion chamber used in the combustion section.
[0010] Figure 4 The diagram illustrates what is suitable for use in Figure 3 The diagram shows a perspective view of the collar used in the auxiliary fuel injector.
[0011] Figure 5 The diagram shows Figure 4 A three-dimensional diagram of the collar, its edge and... Figure 4 The different observation directions in the image indicate different orientations.
[0012] Figure 6 The diagram shows Figure 3 A cross-sectional view of a portion of the combustion chamber, showing the auxiliary fuel injector and the collar. Detailed Implementation
[0013] Before explaining any embodiment of the invention in detail, it should be understood that the invention, in its application, is not limited to the details of the construction and arrangement of the components set forth in this specification or illustrated in the following drawings. The invention can have other embodiments and can be practiced or performed in various ways. Furthermore, it should be understood that the wording and terminology used herein are for descriptive purposes and should not be considered limiting.
[0014] Various techniques relating to the systems and methods will now be described with reference to the accompanying drawings, wherein similar reference numerals consistently denote similar elements. The drawings discussed below in this patent document, as well as the various embodiments used to describe the principles of this disclosure, are merely illustrative and should not be construed as limiting the scope of this disclosure in any way. Those skilled in the art will understand that the principles of this disclosure can be implemented with any suitably arranged device. It should be understood that functions described as being performed by certain system elements can be performed by multiple elements. Similarly, for example, elements can be configured to perform functions described as being performed by multiple elements. Many of the inventive teachings of this application will be described with reference to exemplary, non-limiting embodiments.
[0015] Furthermore, it should be understood that, unless explicitly limited in some examples, the words or phrases used herein should be interpreted broadly. For example, the terms “including,” “having,” and “comprising,” and their derivatives, mean inclusion rather than limitation. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “the” are also intended to include the plural forms. Additionally, the term “and / or” as used herein refers to and covers any and all possible combinations of one or more of the associated listed items. Unless the context clearly indicates otherwise, the term “or” is inclusive, meaning and / or. The phrases “associated with” and “related to,” and their derivatives, can mean including, being included within, interconnected with, containing, contained within, connected to or connected with, linked to or connected with, capable of communicating with, cooperating with, interleaving, juxtaposing, approaching, combining to or combined with, having, possessing the characteristics of, etc. Furthermore, although multiple implementations or configurations may be described herein, any features, methods, steps, components, etc., described with respect to one implementation are equally applicable to other implementations without specific statements to the contrary.
[0016] Furthermore, although the terms “first,” “second,” “third,” etc., may be used herein to refer to various elements, information, functions, or actions, these elements, information, functions, or actions should not be limited by these terms. Rather, these numerical adjectives are used to distinguish different elements, information, functions, or actions from one another. For example, without departing from the scope of this disclosure, a first element, first information, first function, or first action may be referred to as a second element, second information, second function, or second action, and similarly, a second element, second information, second function, or second action may be referred to as a first element, first information, first function, or first action.
[0017] Furthermore, in this specification, the term "axial" or "axially" refers to the direction along the longitudinal axis of the gas turbine engine. The term "radial" or "radially" refers to the direction perpendicular to the longitudinal axis of the gas turbine engine. The term "downstream" or "rearward" refers to the direction along the flow direction. The term "upstream" or "forward" refers to the direction opposite to the flow direction.
[0018] Additionally, unless the context clearly indicates otherwise, the term "adjacent to" can mean: an element is fairly close to another element but not in contact with it; or an element is in contact with another part. Furthermore, unless otherwise clearly stated, the phrase "based on" is intended to mean "at least partially based on". The terms "about" or "approximately" or similar terms are intended to cover variations in the value of the dimension within normal industrial manufacturing tolerances. If no industry standard is available, unless otherwise stated, twenty percent of the variation will fall within the meaning of these terms.
[0019] Figure 1 An example of a gas turbine engine 100 is illustrated, comprising a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a central axis 108. The compressor section 102 includes multiple compressor stages 110, each compressor stage 110 including a set of fixed compressor stator vanes 112 or adjustable guide vanes and a set of rotating compressor blades 114. A rotor 116 supports the rotating compressor blades 114 for rotation about the central axis 108 during operation. In some configurations, a single integral rotor 116 extends the length of the gas turbine engine 100 and is supported for rotation by bearings at either end. In other configurations, the rotor 116 is assembled from several individual spools attached to each other, or may include multiple disc sections attached via one or more bolts.
[0020] Compressor section 102 is in fluid communication with inlet section 118 to allow gas turbine engine 100 to draw atmospheric air into compressor section 102. During operation of gas turbine engine 100, compressor section 102 draws in atmospheric air and compresses it for delivery to combustion section 104. The illustrated compressor section 102 is an example of a compressor section 102, wherein other arrangements and designs are possible.
[0021] In the illustrated configuration, the combustion section 104 includes a plurality of individual combustion chambers 120, each of which operates to mix a fuel stream with compressed air from the compressor section 102 and to burn the air-fuel mixture to produce a high-temperature, high-pressure combustion gas stream or exhaust gas stream 122. Of course, many other arrangements of the combustion section 104 are possible.
[0022] The turbine section 106 includes multiple turbine stages 124, each turbine stage 124 comprising a plurality of stationary turbine stator vanes 126 and a plurality of rotating turbine blades 128. The turbine stages 124 are arranged to receive exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and to expand the gas to convert thermal and pressure energy into rotational or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For a gas turbine engine 100 used for power generation or as a prime mover, the turbine section 106 is also connected to a generator, pump, or other device to be driven. Similar to the compressor section 102, other designs and arrangements of the turbine section 106 are possible.
[0023] An exhaust section 132 is located downstream of turbine section 106 and is arranged to receive the expanded exhaust gas 122 flow from the final turbine stage 124 in turbine section 106. Exhaust section 132 is arranged to effectively guide the exhaust gas 122 away from turbine section 106 to ensure efficient operation of turbine section 106. Many variations and design differences are possible in exhaust section 132. Therefore, the exhaust section 132 illustrated is merely one example of those variations.
[0024] The control system 134 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and control various operations of the gas turbine engine 100. In a preferred configuration, the control system 134 is typically microprocessor-based and includes memory devices and data storage devices for collecting, analyzing, and storing data. Additionally, the control system 134 provides output data to various devices, including monitors, printers, indicators, etc., that allow users to interact with the control system 134 to provide input or adjustment. In the example of a power generation system, the user can input a power output setpoint, and the control system 134 can adjust various control inputs to achieve that power output efficiently.
[0025] The control system 134 can control various operating parameters, including but not limited to variable inlet guide vane position, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 134 also monitors various parameters to ensure proper operation of the gas turbine engine 100. Some of the monitored parameters may include inlet air temperature, compressor outlet temperature and pressure, combustion chamber outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and are recorded for later review if needed.
[0026] Figure 2 The diagram illustrates what is suitable for use in Figure 1 A longitudinal cross-sectional view of the combustion section 200 used in the gas turbine engine 100. The combustion section 200 can be replaced with... Figure 1 Combustion section 104.
[0027] Combustion section 200 includes a housing 202 and combustion chambers 300 enclosed by the housing 202. A plurality of combustion chambers 300 are arranged circumferentially around the central axis 108 of the gas turbine engine 100 and spaced apart from each other to define a canister-type combustion chamber; other arrangements are possible. The plurality of combustion chambers 300 are enclosed by the housing 202. A compressor outlet diffuser 204 is connected to the outlet of the compressor section 102 for supplying compressed air 206 to the combustion chambers 300.
[0028] Each combustion chamber 300 includes a head section 208 connected to a transition duct 210. The head section 208 includes a premixer fuel injector 212, which includes a premixer fuel supply line 214 and an ignition burner 216. The premixer fuel supply line 214 injects fuel into the combustion chamber 300. The fuel is mixed with compressed air 206 and ignited by the ignition burner 216 to generate exhaust gas 218. The transition duct 210 encloses and defines the interior of a combustion chamber 220 through which the exhaust gas 218 passes. The outlet of the transition duct 210 is connected to the inlet of a turbine section 106, allowing the exhaust gas 218 to enter the turbine section 106.
[0029] Combustion chamber 300 includes one or more auxiliary fuel injectors 222 disposed downstream of premixer fuel injector 212 and upstream of transition duct 210. The auxiliary fuel injectors 222 inject further fuel into combustion chamber 220.
[0030] Figure 3 The diagram shows... Figure 2 The combustion chamber 300 shown in the combustion section 200 is a perspective view. The combustion chamber 300 includes a transition outlet frame 302 disposed at the outlet of the transition duct 210. The transition outlet frame 302 is connected to... Figure 2 The turbine section 106 is shown in the figure.
[0031] Combustion chamber 300 includes a collar 400. The collar 400 is fixedly connected to transition pipe 210. The collar 400 can be fixed to transition pipe 210 by welding. Other suitable fixing arrangements can be used to connect collar 400 to transition pipe 210.
[0032] An auxiliary fuel injector 222 is disposed at the transition conduit 210 to allow flow communication with the combustion chamber 220. The auxiliary fuel injector 222 is disposed perpendicular to the transition conduit 210. The auxiliary fuel injector 222 may be disposed at an angle relative to the transition conduit 210. The auxiliary fuel injector 222 has a generally cylindrical shape. A fuel supply line 304 is connected to the fuel booster ring 306 and the auxiliary fuel injector 222 for supplying further fuel to the combustion chamber 220. The auxiliary fuel injector 222 is surrounded by a collar 400. Multiple auxiliary fuel injectors 222 may be circumferentially disposed around the transition conduit 210 and spaced apart from each other. Each auxiliary fuel injector 222 is connected to a fuel supply line 304 and is surrounded by a collar 400.
[0033] Figure 4 The diagram illustrates what is suitable for use in Figure 3 A perspective view of the collar 400 used in the auxiliary fuel injector 222. Figure 5 The diagram shows... Figure 4The three-dimensional view of the collar 400 shown in the figure is along the... Figure 4 The different observation directions in the image indicate different orientations.
[0034] Reference Figure 4 and Figure 5 The collar 400 has a generally cylindrical shape, having a first end 402, a second end 404, and a wall 406 located between the first end 402 and the second end 404. The second end 404 is secured to the transition conduit 210. The first end 402, opposite to the second end 404, is positioned outside the transition conduit 210. The wall 406 is generally annular and encloses the hollow interior for housing the auxiliary fuel injector 222. The wall 406 may be chamfered toward the second end 404 for attaching the collar 400 to the transition conduit 210, for example, by welding. The first end 402 is generally flat. The second end 404 is non-planar. The non-planar shape of the second end 404 mates with the shape of the transition conduit 210 for securing the second end 404 to the transition conduit 210. The non-planar shape includes a saddle shape or a hyperbolic paraboloid shape.
[0035] The collar 400 has an upstream portion 408a and a downstream portion 408b. The upstream portion 408a and the downstream portion 408b are defined relative to the flow direction of the exhaust gas 218. The upstream portion 408a has a larger circumferential length around the periphery of the collar 400 compared to the downstream portion 408b. The upstream portion 408a may also be equal to the downstream portion 408b.
[0036] The collar 400 has a lip 410 extending radially inward from the inner surface of the collar 400 and circumferentially around the inner surface. The lip 410 is located at a first end 402 of the collar 400 and is flush with the first end 402. The lip 410 has a cut 412. The cut 412 may be located at a downstream portion 408b of the collar 400. The location of the cut 412 can be used to identify the downstream portion 408b of the collar 400 (i.e., the orientation of the collar 400) for mounting the collar 400. The cut 412 may also be located at an upstream portion 408a of the collar 400 to identify the upstream portion 408a of the collar 400 when mounting the collar 400. Alternatively, other methods or features (e.g., grooves, markings, notches, etc.) may be formed on the collar 400 to identify the orientation of the collar 400.
[0037] The collar 400 has a baffle 414 extending radially inward from the inner surface of the wall 406 and circumferentially around the inner surface. The baffle 414 divides the interior of the collar 400 into a first cavity 416 and a second cavity 418. The first cavity 416 is defined between a first end 402 and the baffle 414; in fact, the first cavity 416 is defined between a lip 410 and the baffle 414. The second cavity 418 is defined between the baffle 414 and a second end 404. The baffle 414 has a first surface 420 facing the first end 402 of the collar 400 and a second surface 422 facing the second end 404 of the collar 400. The first surface 420 is flat and parallel to the lip 410. The second surface 422 is non-planar. The non-planar shape of the second surface 422 corresponds to the non-planar shape of the second end 404. The non-planar shape includes a saddle shape or a hyperbolic paraboloid shape. Therefore, the distance between the second surface 422 of the baffle 414 and the second end 404 of the collar 400 is constant around the collar 400. This arrangement results in a constant circumferential cross-sectional area of the second cavity 418 (i.e., the area defined between the baffle 414 and the second end 404 of the collar 400, and between the inner surface of the collar 400 and the auxiliary fuel injector 222).
[0038] The collar 400 includes a plurality of upstream orifices 424a and a plurality of downstream orifices 424b. The upstream orifices 424a are at least partially disposed in an upstream portion 408a and cooperate to define a portion of an upstream purging path. The downstream orifices 424b are at least partially disposed in a downstream portion 408b and cooperate to define a portion of a downstream purging path. The upstream orifices 424a and downstream orifices 424b are circumferentially distributed around a wall 406 and spaced apart from each other. The upstream orifices 424a and downstream orifices 424b are disposed in a second cavity 418 of the collar 400. The upstream orifices 424a and downstream orifices 424b allow cooling air 426 to flow from the outside of the collar 400 to the inside of the collar 400.
[0039] The collar 400 includes two ribs 428 extending radially inward from the second surface 422 of the baffle 414 toward the second end 404. The two ribs 428 also extend from the inner surface of the wall 406. The two ribs 428 extend perpendicularly to the second surface 422 of the baffle 414. The two ribs 428 are positioned at two locations on the baffle 414 to space the upstream portion 408a and the downstream portion 408b within the second cavity 418. Figure 4 and Figure 5 As illustrated, the two ribs 428 are positioned downstream of each other with a spacing of less than 180 degrees relative to the flow direction of the exhaust gas 218. Alternatively, the two ribs 428 may be positioned with a spacing of 180 degrees.
[0040] Cooling air 426 is used as purge air to purge collar 400. The flow area of the upstream purge path is defined by the total area of the upstream orifice 424a. The flow area of the downstream purge path is defined by the total area of the downstream orifice 424b. The flow area of the upstream purge path is larger than that of the downstream purge path. This configuration can be achieved by different sizes of the upstream orifice 424a and downstream orifice 424b, different total numbers of the upstream orifice 424a and downstream orifice 424b, different circumferential lengths of the upstream portion 408a and downstream portion 408b, or combinations thereof.
[0041] like Figure 4 and Figure 5 As illustrated, the upstream orifice 424a is larger than the downstream orifice 424b. Each upstream orifice 424a has a first diameter, and each downstream orifice 424b has a second diameter smaller than the first diameter. The total number of upstream orifices 424a provided in the upstream portion 408a is greater than the total number of downstream orifices 424b provided in the downstream portion 408b. The distance between adjacent upstream orifices 424a is equal. The distance between adjacent downstream orifices 424b is equal. The distance between adjacent upstream orifices 424a is less than the distance between adjacent downstream orifices 424b. The upstream portion 408a has a larger circumferential length around the periphery of the collar 400 compared to the downstream portion 408b. Two ribs 428 separate the upstream portion 408a and the downstream portion 408b in the second cavity 418. Other arrangements are also possible to achieve a flow area in the upstream purge path that is larger than that in the downstream purge path.
[0042] Figure 6 The diagram shows a cross-sectional view of a portion of the combustion chamber 300, illustrating the auxiliary fuel injector 222 and the collar 400. Fuel is supplied to the auxiliary fuel injector 222 via fuel supply line 304. The auxiliary fuel injector 222 provides further fuel to the exhaust gas 218 downstream of the premixer fuel injector 212 to improve overall combustion in the combustion chamber 220.
[0043] The collar 400 receives a sealing ring 602, a gasket ring 604, and a snap-fit ring 606, each disposed in a first cavity 416 between the lip 410 and the baffle 414. The sealing ring 602 is disposed on the baffle 414. The gasket ring 604 is disposed on the sealing ring 602. The snap-fit ring 606 is disposed on the gasket ring 604. The lip 410 holds the sealing ring 602, gasket ring 604, and snap-fit ring 606 within the first cavity 416. A notch 412 is used for assembling and disassembling the sealing ring 602, gasket ring 604, and snap-fit ring 606 disposed in the first cavity 416 of the collar 400.
[0044] An auxiliary fuel injector 222 is disposed in an opening 608 defined by a transition conduit 210. A gap 610 exists between the auxiliary fuel injector 222 and the opening 608. The opening 608 has an upstream side and a downstream side defined by the flow direction of the exhaust gas 218.
[0045] The second end 404 of the collar 400 is secured to the transition pipe 210 around the opening 608. The first end 402 of the collar 400, opposite to the second end 404, is positioned outside the transition pipe 210. The collar 400 is oriented such that the upstream portion 408a faces the upstream side of the opening 608 and the downstream portion 408b faces the downstream side of the opening 608.
[0046] Upstream orifice 424a and downstream orifice 424b extend through collar 400. The outlets of upstream orifice 424a and downstream orifice 424b are located in the second cavity 418 of collar 400. Upstream orifice 424a and downstream orifice 424b are inclined relative to the flow direction of exhaust gas 218. Upstream orifice 424a and downstream orifice 424b are oriented such that cooling air 426 exits from upstream orifice 424a and downstream orifice 424b in a direction toward transition conduit 210.
[0047] In the operation of the gas turbine engine 100 and referring to Figure 2 Compressed air 206 enters the head section 208 and mixes with fuel injected from the premixer fuel supply pipe 214. The air / fuel mixture is ignited by the igniter burner 216 to form exhaust gas 218. Exhaust gas 218 flows in the flow direction within the transition duct 210. [Turn to...] Figure 6Exhaust gas 218 can enter the second chamber 418 of the collar 400 through the gap 610 between the auxiliary fuel injector 222 and the transition duct 210. This may result in the intake of exhaust gas 218. Cooling air 426 flows from the outside of the transition duct 210 into the second chamber 418 through an upstream purge path defined by an upstream orifice 424a. Cooling air 426 also flows from the outside of the transition duct 210 into the second chamber 418 through a downstream purge path defined by a downstream orifice 424b. Cooling air 426 is used as purge air to purge the second chamber 418 of the collar 400. Purge reduces the intake of exhaust gas 218. Sealing ring 602 allows cooling air 426 to flow from the outside of the transition duct 210 into the second chamber 418 through the upstream orifice 424a and the downstream orifice 424b. Sealing ring 602 also seals the cooling air 426 and exhaust gas 218 within the second chamber 418. Cooling air 426 is the flow of compressed air 206 used to cool the transition duct 210. After the second chamber 418 of the purge ring 400, cooling air 426 flows into the transition duct 210 and mixes with exhaust gas 218 in the combustion chamber 220. Cooling air 426 participates at least partially in the combustion process of the fuel injected into the exhaust gas 218 by the auxiliary fuel injector 222. The mixture of cooling air 426 and exhaust gas 218 continues in the flow direction and eventually exits the combustion chamber 300 at the transition outlet frame 302 and enters the turbine section 106, as shown below. Figure 2 and Figure 3 As shown in the figure.
[0048] In some configurations, an asymmetric purge flow through the collar 400 is desired. The upstream portion 408a of the collar 400 has a greater intake of exhaust gas 218 compared to the downstream portion 408b. Therefore, the upstream portion 408a requires a higher purge flow compared to the downstream portion 408b. The larger flow area of the upstream purge path provides a larger purge flow to the upstream portion 408a. The smaller flow area of the downstream purge path provides a smaller purge flow to the downstream portion 408b. The arrangement of the upstream and downstream purge paths conforms to the asymmetric purge expectation through the collar 400, thereby reducing the consumption of cooling air 426.
[0049] The second chamber 418 is separated by two ribs 428. Without the two ribs 428, the cooling air 426 in the upstream portion 408a communicates with the cooling air 426 in the downstream portion 408b due to the lower static pressure in the downstream portion 408b. With the two ribs 428, the cooling air 426 in the upstream portion 408a remains in the upstream portion 408a and does not communicate with the cooling air 426 in the downstream portion 408b. The constant circumferential cross-sectional area of the second chamber 418 improves the distribution of the cooling air 426 within the second chamber 418 to provide effective cooling and purging.
[0050] The asymmetrical and spaced collar 400 improves purging performance in the gap 610 and reduces the intake of exhaust gas 218 into the collar 400. The asymmetrical and spaced collar 400 reduces cooling air 426 consumption and improves overall combustion. The asymmetrical and spaced collar 400 increases the design life of the gas turbine engine 100. The asymmetrical and spaced collar 400 can control the amount of cooling air 426 used as purging air to meet purging requirements.
[0051] Although exemplary embodiments of the present disclosure have been described in detail, those skilled in the art will understand that various modifications, alternatives, variations and improvements disclosed herein can be made without departing from the spirit and scope of the broadest form of the disclosure.
[0052] Nothing described in this application should be construed as implying that any particular element, step, action, or function is a fundamental element that must be included within the scope of the claims: the scope of the patent subject matter is defined only by the permissible claims. Furthermore, unless the exact phrase "means for…" is followed by a participle, these claims are not intended to invoke a claim construction of means plus function.
[0053] List of Components in the Attachment
[0054] 100 gas turbine engine
[0055] 102 Compressor Section
[0056] 104 Combustion Section
[0057] 106 Turbine Section
[0058] 108 central axis
[0059] 110 compressor stage
[0060] 112 Fixed Compressor Stationary Vane
[0061] 114 Rotary Compressor Blades
[0062] 116 rotor
[0063] 118 Entrance Section
[0064] 120 Combustion Chamber
[0065] 122 exhaust gas
[0066] 124 turbo-grade
[0067] 126 Fixed Turbine Stator
[0068] 128 rotating turbine blades
[0069] 130 Turbo Inlet
[0070] 132 exhaust section
[0071] 134 Control System
[0072] 200 Combustion Section
[0073] 202 shell
[0074] 204 compressor outlet diffuser
[0075] 206 Compressed Air
[0076] 208 head end section
[0077] 210 transition pipe
[0078] 212 premixer fuel injector
[0079] 214 Premixer Fuel Supply Pipe
[0080] 216 Ignition Burner
[0081] 218 exhaust gas
[0082] 220 combustion chamber
[0083] 222 Auxiliary Fuel Injector
[0084] 300 combustion chamber
[0085] 302 Transitional Export Framework
[0086] 304 fuel supply pipe
[0087] 306 fuel booster ring
[0088] 400 rings
[0089] 402 First end
[0090] 404 Second End
[0091] 406 wall
[0092] 408a upstream section
[0093] 408b downstream section
[0094] 410 Lip Edge
[0095] 412 incision
[0096] 414 baffle
[0097] 416 First Cavity
[0098] 418 Second Chamber
[0099] 420 First Surface
[0100] 422 Second Surface
[0101] 424a upstream orifice
[0102] 424b downstream orifice
[0103] 426 Cooling Air
[0104] 428 ribs
[0105] 602 sealing ring
[0106] 604 gasket ring
[0107] 606 buckle ring
[0108] 608 opening
[0109] 610 gap
Claims
1. A combustion chamber, comprising: A premixed fuel injector that injects fuel into the combustion chamber and ignites the mixture of fuel and compressed air to produce exhaust gas; A transition duct that defines the interior through which the exhaust gas passes, and an opening through which the transition duct passes, the opening having an upstream side and a downstream side defined by the flow direction of the exhaust gas; An auxiliary fuel injector, disposed in the opening, injects further fuel into the exhaust gas; and A collar, fixedly connected to and positioned around the auxiliary fuel injector, has a first end positioned outside the transition conduit, a second end fixed to the transition conduit around the opening, and a wall between the first and second ends. The collar cooperates with the auxiliary fuel injector to define an upstream purge path at least partially located on the upstream side and a downstream purge path at least partially located on the downstream side. The upstream and downstream purge paths each provide flow communication between the outside and inside of the transition conduit, with the upstream purge path having a larger flow area compared to the downstream purge path. The collar includes a baffle extending from the inner surface of the collar and circumferentially around the inner surface, wherein the baffle divides the interior of the collar into a first cavity located between the baffle and the first end and a second cavity located between the baffle and the second end. The collar includes two ribs extending from the inner surface of the collar and from the surface of the baffle facing the second end of the collar, wherein the upstream purge path and the downstream purge path are defined in the second cavity and separated by the two ribs.
2. The combustion chamber according to claim 1, wherein, The collar includes a plurality of upstream orifices facing the opening on the upstream side and a plurality of downstream orifices facing the opening on the downstream side, wherein the plurality of upstream orifices define the upstream purging path and the plurality of downstream orifices define the downstream purging path.
3. The combustion chamber according to claim 2, wherein, The size of each of the plurality of upstream orifices is greater than the size of each of the plurality of downstream orifices.
4. The combustion chamber according to claim 2, wherein, The total number of the multiple upstream orifices is greater than the total number of the multiple downstream orifices.
5. The combustion chamber according to claim 2, wherein, The plurality of upstream and downstream orifices extend through the wall and are inclined relative to the flow direction of the exhaust gas.
6. The combustion chamber according to claim 1, wherein, The upstream purging path has a larger circumferential length around the periphery of the collar compared to the downstream purging path.
7. The combustion chamber according to claim 1, wherein, The surface of the baffle facing the second end of the collar has a shape corresponding to the shape of the second end, so as to form a constant circumferential cross-sectional area of the second cavity.
8. The combustion chamber according to claim 1, wherein, The two ribs are positioned at the downstream side with a spacing of less than 180 degrees between them.
9. A combustion chamber, comprising: A transition conduit defines an interior through which a flow of combustion gases passes in the flow direction, the transition conduit defining an opening through which the transition conduit passes, the opening having an upstream side and a downstream side defined by the flow direction; An auxiliary fuel injector, which is at least partially disposed within the opening to inject fuel into the flow of combustion gases; as well as A collar, fixedly connected to the transition conduit and positioned around the opening, cooperates with the auxiliary fuel injector to define an upstream purge path at least partially located on the upstream side of the opening and a downstream purge path at least partially located on the downstream side of the opening, the upstream and downstream purge paths each providing flow communication between the exterior and interior of the transition conduit, the upstream purge path having a larger flow area compared to the downstream purge path. The collar includes a baffle extending from the inner surface of the collar and circumferentially around the inner surface. The baffle divides the interior of the collar into a first cavity between the baffle and a first end of the collar, and a second cavity between the baffle and a second end of the collar. The collar includes two ribs extending from the inner surface of the collar and from the surface of the baffle facing the second end of the collar, wherein the upstream purge path and the downstream purge path are defined in the second cavity and separated by the two ribs.
10. The combustion chamber according to claim 9, wherein, The collar includes a plurality of upstream orifices facing the opening on the upstream side and a plurality of downstream orifices facing the opening on the downstream side, wherein the plurality of upstream orifices define the upstream purging path and the plurality of downstream orifices define the downstream purging path.
11. The combustion chamber according to claim 10, wherein, The size of each of the plurality of upstream orifices is greater than the size of each of the plurality of downstream orifices.
12. The combustion chamber according to claim 10, wherein, The total number of the multiple upstream orifices is greater than the total number of the multiple downstream orifices.
13. The combustion chamber according to claim 10, wherein, The plurality of upstream and downstream orifices extend through the collar and are inclined relative to the flow direction of the combustion gas.
14. The combustion chamber according to claim 9, wherein, The upstream purging path has a larger circumferential length around the periphery of the collar compared to the downstream purging path.
15. The combustion chamber according to claim 9, wherein, The first end is positioned outside the transition pipe, and the second end is fixed to the transition pipe.
16. The combustion chamber according to claim 9, wherein, The surface of the baffle facing the second end of the collar has a shape corresponding to the shape of the second end, so as to form a constant circumferential cross-sectional area of the second cavity.
17. The combustion chamber according to claim 9, wherein, The two ribs are positioned at the downstream side with a spacing of less than 180 degrees between them.
18. A combustion chamber, comprising: A transition conduit defines an interior through which a flow of combustion gases passes in the flow direction, the transition conduit defining an opening through which the transition conduit passes, the opening having an upstream side and a downstream side defined by the flow direction; An auxiliary fuel injector, which is at least partially disposed within the opening to inject fuel into the flow of combustion gases; as well as A collar, fixedly connected to the transition conduit and positioned around the opening, cooperates with the auxiliary fuel injector to define an upstream purge path at least partially located on the upstream side of the opening and a downstream purge path at least partially located on the downstream side of the opening, the upstream and downstream purge paths each providing flow communication between the exterior and interior of the transition conduit, the upstream purge path having a larger flow area compared to the downstream purge path. The collar includes a plurality of upstream openings facing the opening on the upstream side and a plurality of downstream openings facing the opening on the downstream side. Wherein, the plurality of upstream orifices define the upstream purging path, and the plurality of downstream orifices define the downstream purging path. Wherein, the size of each of the plurality of upstream orifices is larger than the size of each of the plurality of downstream orifices. Wherein, the total number of the plurality of upstream orifices is greater than the total number of the plurality of downstream orifices. The upstream purging path has a larger circumferential length around the periphery of the collar compared to the downstream purging path. The upstream purging path and the downstream purging path are separated by two ribs disposed on the inner surface of the collar. The collar includes a baffle extending from the inner surface of the collar and circumferentially around the inner surface. The baffle divides the interior of the collar into a first cavity between the baffle and a first end of the collar, and a second cavity between the baffle and a second end of the collar. The two ribs extend from the inner surface of the collar and from the surface of the baffle facing the second end of the collar, and the upstream purge path and the downstream purge path are defined in the second cavity and separated by the two ribs.