Fuel injector with an igniter for a combustion chamber of a gas turbine.

专利摘要:
A fuel injector (68) for a combustor of a gas turbine includes an annular main body (72). A fluid supply channel (94) extends at least partially through the main body (72). An axially extending inner body (84) extends inside the main body (72). The inner body (84) at least partially defines an inner chamber (90) that extends at least partially through the inner body (84). The inner chamber (90) is in fluid communication with the fluid supply channel (94). A retractable igniter (70) extends straight outwardly from the inner chamber (90) when the fluid supply channel (94) is pressurized.
公开号:CH707454B1
申请号:CH02158/13
申请日:2013-12-30
公开日:2017-10-31
发明作者:Marie Graham Kaitlin；Scott Flanagan James；Scott Lebegue Jeffrey
申请人:Gen Electric；
IPC主号:

专利说明:

Description Field of the Invention The present invention relates generally to a gas turbine engine. More particularly, this invention relates to a fuel injector having an igniter for a combustor of a gas turbine.
Background of the Invention Turbine systems are commonly used in the fields of, for example, power generation. A typical gas turbine includes a compressor section, a combustion section downstream of the compressor section, and a turbine section downstream of the combustion section. At least one shaft extends at least partially axially through the gas turbine. A generator / motor is coupled to the shaft at one end. The compressor section includes an inlet defined at an upstream end of the compressor section. The combustion section generally includes a housing and a plurality of combustion chambers disposed in an annular array about the housing.
Each combustion chamber includes an end cover which is connected to the housing. At least one fuel nozzle extends substantially axially downstream of the end cover and at least partially through a cap assembly extending radially inward of the combustor downstream of the end cap. An annular liner, such as a combustion liner and / or transition piece, extends downstream of the cap assembly to at least partially define the combustion chamber and / or a hot gas path through the combustion chamber. The liner terminates substantially at a location adjacent to an inlet of the turbine section. In some gas turbine designs, a series of rollover tubes extend through the liner and housing between all or some of the multiple combustors to define a flow path between adjacent combustors. At or adjacent to the combustion chamber of one of the plurality of combustion chambers, a spark plug is disposed.
During the start or ignition of the combustion section, the generator / motor rotates the shaft to drive the compressor section. A working fluid, such as air, is drawn in through the inlet of the compressor section and is increasingly compressed as it flows through the compressor section toward the combustion section. The compressed air is directed into the combustion section housing where it is split between the individual combustion chambers of the combustion section. The compressed air is mixed with a fuel to form a combustible mixture within the combustion chamber of each combustion chamber. The spark plug is energized to ignite the combustible mixture within the respective combustion chamber. A flame then propagates through the rollover tubes to ignite the adjacent combustion chambers in rows until each combustion chamber of the combustion section is lit.
The spark plug and the rollover pipes as a system are generally effective for igniting the combustion portion of the gas turbine. However, various problems can arise with flashover ignition systems, particularly in combustors that use late lean technology, increase costs, and impose undesirable limitations on combustion developers. For example, such problems may include varying rates of thermal expansion of adjacent combustors that may result in leakage around the rollover tubes, and also the risk of sparkover by the rollover tubes of adjacent combustors after ignition, rinsing of the rollover tubes after blowing out one or more of the combustors, include re-igniting a combustor after a blow-off event and / or cooling the rollover tubes during operation of the gas turbine. In addition, various current spark plug designs may be supplied with breakthrough formation through the housing and / or through the end cap, thereby forming an additional potential leakage area. Accordingly, an improved system for igniting the combustors of the gas turbine would be useful in the art.
Brief Description of the Invention Aspects and advantages of the invention are set forth below in the description which follows, or may be obvious from the description, or may be learned by practice of the invention.
One aspect of the present invention is a fuel injector for a combustor of a gas turbine. The fuel injector includes an annular main body that at least partially defines a flow path through the fuel injector. A fluid supply channel extends outside the flow path at least partially through the main body and can be acted upon with fluid. Inside the main body extends an axially extending inner body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the Fluidzuführkanal. A retractable igniter extends straight outwardly from the inner chamber into the flow path when fluid is supplied to the fluid supply passage.
Particularly preferred embodiments of the fuel injector according to the first aspect of the present invention include one or more of the following components: The fuel injector may include a spring disposed within the inner chamber, wherein the spring is coupled to the igniter.
The fuel injector may further include a radially extending pressure plate disposed within the inner chamber, wherein the pressure plate is disposed on the igniter and surrounds the igniter at least partially in the circumferential direction.
The fluid supply passage may be in fluid communication with at least one of a liquid fuel source, a gaseous fuel source or a compressed working fluid source in the operating condition of the fuel injector.
The upstream end of the inner body may be dome-shaped.
The fuel injector may further include an annular flow path formed at least partially between the main body and the inner body.
The fuel injector may further include a fuel supply line and at least one fuel injection port, wherein the at least one fuel injection port defines a fluid communication between the fuel supply line and the annular flow path of the fuel injector.
The main body may include an upstream end that is axially separated from a downstream end, the igniter extending downstream from the downstream end of the main body when fluid is supplied to the fluid supply channel.
Another aspect of the present invention is a combustor for a gas turbine. The combustion chamber generally includes an end cover connected to a housing. A fuel nozzle extends downstream from the end cap. A cap assembly at least partially surrounds a portion of the fuel nozzle. An annular liner extends downstream of the cap assembly. A fuel injector extends substantially radially through the liner. The fuel injector includes an annular main body that at least partially defines a flow path through the fuel injector. The annular main body includes a downstream end. A fluid supply channel which can be acted upon with fluid extends outside the flow path at least partially through the main body. An inner body is disposed within the flow path of the main body. The inner body has an opening at a downstream end of the inner body. An inner chamber in fluid communication with the fluid supply passage is defined at least partially inside the inner body. A retractable igniter is disposed inside the inner chamber. The igniter extends straight through the opening of the inner body and at least partially into the flow path of the main body when fluid is supplied to the fluid supply passage.
Particularly preferred embodiments of the combustion chamber according to the second aspect of the present invention may include those of the fuel injector according to the first aspect and in particular contain one or more of the following components: The lining is preferably either a combustion liner or a transitional channel or a transition nozzle ,
The fuel injector may further comprise a spring which is disposed inside the inner chamber, wherein the spring is connected to the igniter.
The fuel injector may further include a pressure plate disposed inside the inner chamber, the pressure plate at least partially surrounding the igniter in the circumferential direction.
The fluid circuit of the fuel injector may be in fluid communication with at least one of a liquid fuel source, a gaseous fuel source, or a compressed working fluid source.
The inner chamber of the fuel injector may have a domed shaped upstream end.
The fuel injector may further include a fuel supply line and at least one fuel injection port, wherein the at least one fuel injection port defines fluid communication between the fuel supply line and the flow path of the fuel injector.
The retractable igniter of the fuel injector may extend downstream from the downstream end of the main body when fluid is supplied to the fluid supply passage.
Yet another aspect of the present invention includes a gas turbine. The gas turbine generally includes a compressor section, a combustion section downstream of the compressor section, and a turbine section downstream of the combustion section. The combustion section includes at least one combustion chamber, wherein the combustion chamber has at least one annular liner that at least partially defines a hot gas path through the combustion chamber. A fuel injector extends at least partially through the lining of the combustion chamber. The fuel injector includes an annular main body that at least partially defines a flow path through the fuel injector. A fluid supply channel which can be acted upon with fluid extends outside the flow path at least partially through the main body. An inner body extends axially inside the main body. An inner chamber in fluid communication with the fluid supply channel is defined at least partially inside the inner body. A retractable igniter moves linearly outwardly from the inner chamber into the flow path of the main body in the direction of the hot gas path in motion, when fluid is supplied to the fluid supply passage.
Particularly preferred embodiments of the gas turbine according to the third aspect of the present invention may include those of the fuel injector and the combustion chamber according to the first and the second aspect, and in particular contain one or more of the following components: The fuel injector may further comprise a spring which is disposed inside the inner chamber of the fuel injector.
The fluid supply channel may be in fluid communication with at least one of a liquid fuel source and / or a gaseous fuel source and / or a compressed working fluid source.
The fuel injector may further include a fuel circuit and at least one fuel injection port, wherein the fuel injection port defines a fluid communication between the fuel supply line and the flow path of the fuel injector.
Those skilled in the art will recognize the features and aspects of such embodiments upon review of the specification.
BRIEF DESCRIPTION OF THE DRAWINGS A full and transposable disclosure of the present invention, including the best mode thereof, will be set forth in greater detail by those skilled in the art in the remainder of the specification, which includes reference to the accompanying drawings in which: FIG :
1 is a functional block diagram of an exemplary gas turbine that may incorporate various embodiments of the present invention;
FIG. 2 is a simplified cross-sectional side view of an exemplary combustor incorporating various embodiments of the present invention; FIG.
3 is a plan view from the upstream direction of a fuel injector according to at least one embodiment of the present invention;
Fig. 4 is a side cross-sectional view of the fuel injector as illustrated in Fig. 3; and
5 is a cross-sectional side view of the fuel injector, as illustrated in FIG. 4, according to at least one embodiment of the present invention.
DETAILED DESCRIPTION OF THE INVENTION Reference will now be made in detail to the present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses terms in the form of numbers and letters to refer to features in the drawings. Like or similar terms in the drawings and the description are used to refer to the same or similar parts of the invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one component from another, and are not intended to indicate location or importance of the individual components. In addition, the terms "upstream" and "downstream" refer to the relative position of the components in a fluid path. For example, a component A is upstream of a component B when a fluid flows from component A to component B. Inversely, component B is downstream of component A when component B receives fluid flow from component A.
Each example is intended to illustrate the invention, not for the purpose of limiting the invention. In fact, it will be apparent to those skilled in the art that modifications and changes may be made to the present invention without departing from the scope or scope thereof. For example, features illustrated or described as part of one embodiment may be used in another embodiment to yield a still further embodiment. Although exemplary embodiments of the present invention are described generally in the context of a fuel injector incorporated into an industrial gas turbine, one skilled in the art will readily appreciate from the teachings herein that embodiments of the present invention are not limited to an industrial gas turbine are.
Reference is now made to the drawings, in which identical reference numerals denote the same elements throughout the figures. FIG. 1 shows a functional block diagram of an exemplary gas turbine engine 10 that may incorporate various embodiments of the present invention. As illustrated, the gas turbine engine 10 generally includes an inlet section 12 that may include a number of filters, cooling loops, liquid separators, and / or other devices to purify and process a working fluid (eg, air) 14 entering the gas turbine engine 10 to prepare in any other way. The working fluid 14 flows to a compressor section in which a compressor 16 increasingly imparts kinetic energy to the working fluid to produce a compressed working fluid 18 in a high energy state.
The compressed working fluid 18 is mixed with a fuel from a fuel delivery system 20 to form a combustible mixture within one or more combustion chambers 22. The combustible mixture is burned to produce combustion gases 24 having a high temperature and a high pressure. The combustion gases 24 pass through a turbine 26 of a turbine section to perform work. For example, the turbine 26 may be connected to a shaft 28 that drives the compressor 16 to produce the compressed working fluid 18, thereby maintaining the combustion process. Alternatively or additionally, the shaft 28 may connect the turbine 26 to a generator 30 for generating electricity. Exhaust gases 32 from the turbine 26 pass through an exhaust section 34 which connects the turbine 26 to an exhaust stack 36 downstream of the turbine 26.
The combustors 22 may include any type of combustor as known in the art, and the present invention is not limited to any particular combustor design. FIG. 2 shows a simplified cross-sectional side view of an exemplary combustor 22 incorporating various embodiments of the present invention. As illustrated in FIG. 2, a housing 40 and an end cover 42 may be combined to receive the compressed working fluid 18 that flows to the combustion chamber 22 from the compressor 16 (FIG. 1). The end cover 42 may be in fluid communication with the fuel supply 20.
At least one primary fuel nozzle 44 extends substantially in the axial direction downstream of an inner surface 46 of the end cover 42. A radially extending cap assembly 48 at least partially surrounds at least a portion of the primary fuel nozzles 44. An annular liner 50 extends downstream from the Cap assembly 48 toward an inlet 51 of the turbine 26 (Fig. 1). The liner 50 at least partially defines a hot gas path 52 that extends through the combustor 22 and into the turbine 26 (FIG. 1). The liner 50 may be a single component, such as a transition nozzle, or may include multiple interconnected components. For example, the liner 50 may include a combustion liner connected to a transition duct and / or a transition nozzle.
Within the liner 50, a combustion zone 54 is defined downstream of the cap assembly 48 and / or the primary fuel nozzles 44. In certain combustor configurations, at least one annular sleeve 56, such as a flow sleeve or an impact sleeve, at least partially surrounds the liner 50 to at least partially define a cooling flow path 58 therebetween. Multiple cooling holes 60 may extend through the sleeve 56 to direct the compressed working fluid 18 into the cooling flow path 58 and toward the end cover 42 to achieve cooling on the liner 50.
In certain embodiments, as illustrated in FIG. 2, a secondary fuel nozzle or injector 62 extends at least partially through the liner 50 and / or at least partially through the annular sleeve 56. The fuel injector 62 may extend through the liner 50 and / or the annular sleeve 56 at any location downstream of the cap assembly 48. For example, the fuel injector may extend through the liner 50 at a location that is substantially proximate the combustion zone 54. The fuel injector 62 is in fluid communication with the fuel supply 20 or with an alternative fuel supply (not illustrated) through one or more fluid couplings 64, such as fluid lines and / or valves. In certain embodiments, a flow control valve is fluidly connected to the one or more fluid couplings 64 to control a flow rate of the fuel to the fuel injector 62 during operation of the combustion chamber 22. In certain embodiments, the combustor 22 may include a plurality of the fuel injectors 62 that extend substantially radially through the liner 50 and / or the annular sleeve 56 generally downstream of the cap assembly 48.
In embodiments of the invention, as illustrated in FIG. 2, the combustor includes a secondary fuel nozzle or injector 68 containing a retractable igniter. FIG. 3 illustrates a perspective view of the fuel injector 68 as illustrated in FIG. 2 with a retractable igniter 70 according to at least one embodiment of the present invention, and FIG. 4 shows a cross-sectional side view of the fuel injector 68 illustrated in FIG extends at least partially through a portion of the liner 50 according to various embodiments of the present invention. As illustrated in FIGS. 3 and 4, the fuel injector 68 generally includes an annular main body 72 having an upstream end 74 that is axially separated from a downstream end 76 with respect to an axial centerline of the main body 72. The main body 72 at least partially defines a flow path 78 that extends through the fuel injector 68. The main body 72 further includes at least one fuel supply line 80 extending at least partially through the main body 72. The fuel supply line 80 is in fluid communication with the fuel supply 20 or an alternative fuel source (not illustrated). A plurality of fuel injection ports 82 provide fluid communication between the fuel supply line 80 and the flow path 78 extending through the main body 72.
As illustrated in FIGS. 3 and 4, an axially extending inner body 84 extends at least partially through the flow path 78 of the main body 72. The inner body 84 and the main body 72 may be molded and / or machined as a single component or manufactured as separate components. The flow path 78 may be defined at least partially between the inner body 84 and the main body 72. As illustrated in FIG. 4, the inner body 82 generally includes an upstream end 86 and a downstream end 88. In certain embodiments, the upstream end 86 of the inner body 84 is configured substantially dome-shaped.
As illustrated in FIG. 4, the inner body 84 at least partially defines an inner chamber 90. The inner chamber 90 extends substantially axially within the inner body 84. An opening 92 at the downstream end 88 of the inner body 84 provides fluid communication between the inner chamber 90 and the flow path 78 of the main body 72 of the fuel injector 68 and / or the hot gas path 52 of the combustion chamber 22 (FIG. 2). In some configurations, multiple swirler vanes may extend between the main body 72 and the inner body 84 within the flow path 78 of the main body 72.
A fluid supply channel 94 in fluid communication with the fuel supply 20 or with an alternative fuel or air supply (not illustrated) extends at least partially through the main body 72. At least one inlet port 96 provides fluid communication between the fluid supply channel 94 and the interior chamber 90. The fuel inlet 20 may be configured to include at least one of a liquid fuel and / or a gaseous fuel and / or a compressed working fluid, such as compressed air Fluid supply channel 94 to deliver. The fluid supply channel 94 may be in fluid communication with the fuel supply line 80 of the main body 72 or may be a separate supply.
As illustrated in FIGS. 3 and 4, the retractable igniter 70 is at least partially disposed within the interior chamber 90. The igniter 70 may be an igniter of any type that is suitable for use within the operating environment of the combustor 22. For example, the igniter 70 may be an electric spark igniter. As illustrated in FIG. 4, igniter 70 generally includes an upper portion 98, a lower portion 100, and a firing tip 102 that extends straight from lower portion 100. The igniter 70 may have any cross-sectional shape. For example, igniter 70 may be cylindrical, triangular, rectangular, or any combination of these. The igniter 70 may be connected to an electrical power source (not illustrated) via a wire 104 extending through the inner body 84. In certain embodiments, the wire 104 extends through the upstream end 86 of the inner body 84 and is connected to the upper portion 98 of the igniter 70. The wire 104 may be wound within the inner chamber 90 to allow linear movement of the igniter 70 when the fluid supply channel 94 is pressurized.
In certain embodiments, a spring 106 is disposed inside the inner chamber 90 of the inner body 84. The spring 106 may be a spring of any type suitable for practicing the present invention. For example, the spring 106 may be a helical compression spring, a tension spring, a spring washer, or a wave spring. The spring 106 at least partially surrounds a portion of the igniter 70 within the interior chamber 90. In certain embodiments, the spring 106 is connected to the ignitor 70 to hold the ignitor 70 in place and / or to provide a retracting force to the ignitor 70 ,
The inner body 84 may be configured to clamp at least one end of the spring 106. For example, a retainer 108, such as a slot or shoulder, may be formed at least partially inside the inner body 84 to hold the spring 106 in place within the inner chamber 90. The retainer 108 may be positioned toward the upstream end 86 or the downstream end 88 of the inner body 84. In certain embodiments, a radially extending pressure plate 110 at least partially surrounds the igniter 70 within the inner chamber 90 in the circumferential direction. The pressure plate 110 may be attached to the igniter 70 and / or the spring 106.
As illustrated in Figure 4, the igniter 70, particularly the lower portion of the igniter, is substantially surrounded by the inner body 84 when the fluid delivery channel 94 is passive or unencumbered. In this way, the igniter 70, in particular the lower portion 100 and / or the firing tip 102, is at least partially shielded from the hot gases flowing through the hot gas path 52 of the combustion chamber 22. As a result, thermal stresses on the igniter 70 during operation of the combustor 22 may be reduced, thereby increasing the mechanical life of the igniter 70.
FIG. 5 shows a cross-sectional side view of the fuel injector 68 illustrated in FIG. 4 with the fluid supply duct 94 acted upon, for example during ignition of the combustion chamber. In one embodiment, the fuel 112 is directed from the fuel supply 20 into the fluid supply channel 94. The fuel 112 flows through the inlet ports 96 and into the interior chamber 90. The fuel flows between the igniter 70 and the inner chamber 90 toward the upstream end 86 of the inner body 84 and toward the upper portion of the igniter 70.
The fuel pressurizes the inner chamber, thereby exerting an axial force on the upper portion 98 of the igniter 70 and / or on the pressure plate 110. The axial force overcomes an opposing axial force exerted by the spring 106, thereby causing a portion of the igniter 70 including the lower portion 100 and / or the firing tip 102 to extend straight through the opening 92 of the inner body 84 , In certain embodiments, the lower portion 100 and / or the firing tip 102 extends into the flow path 78 that is at least partially defined between the main body 72 and the inner body 84 of the fuel injector 68. In further embodiments, the lower portion 100 and / or the firing tip 102 extends into the hot gas path 52 and / or into the combustion zone 54 (FIG. 2) of the combustor 22.
Fuel is delivered to the combustion zone 54 (FIG. 2) through one or more of the primary fuel nozzles 44 (FIG. 2) and / or through the one or more fuel injection ports 82 of the fuel injector 68. The igniter 70 is energized via the wire 104, thereby causing a high voltage spark to emanate from the firing tip 102, thereby igniting the fuel in the combustion zone 54 and / or within the flowpath 78. As soon as the combustion chamber 22 (FIG. 2) is ignited, the fuel supply 20, which supplies the fuel to the fluid supply channel 94, can be switched off. As a result, the pressure inside the inner chamber is reduced or eliminated, and the spring force 116 causes the ignitor 70 to retract to its original position as illustrated in FIG. 4. In modified embodiments, the flow rate of the fuel may be increased or decreased to adjust the position of the firing tip 102.
In modified embodiments, the fluid supply channel 94 remain energized after ignition of the combustion chamber 22. In this way, the fuel 112 flowing from the inner chamber through the opening of the inner body can achieve beneficial cooling at the lower portion and / or the firing tip of the igniter. Additionally or alternatively, the compressed working fluid 18 may be directed through the main body flow path 78, or a compressed working fluid, such as air, may be directed through the fuel supply 20 to the fluid supply channel for cooling at the lower portion 100 and / or the firing tip 102 to achieve the detonator.
The invention, as illustrated in FIGS. 2-5 and as described herein, provides various technical advantages over existing fuel injectors and ignition systems currently used for gas turbine combustors. For example, the fuel injector 68 with the retractable igniter 70 may be mounted in an existing secondary fuel injector or fuel injector 62 within the lining of the combustor, for example, in a late lean-mixed fuel injection system, thereby eliminating the need for an igniter-introduced igniter, as currently used in many gas turbine combustor designs is eliminated. In addition, the compact / integrated design of the fuel injector 68 allows installations within each combustion chamber of the combustion section, thereby eliminating the need for flashover pipes between adjacent combustion chambers. As a result, the risk of persistent flashover flow between rollover pipes and the combustor flow / mixing problems associated with scavenging / cooling the rollover pipes can be improved and / or eliminated. In addition, the fuel injector 68 allows combustion chamber combustion chambers to fire independently in the event of a single combustion chamber blowout event, thereby improving recovery time from such an event. In addition, the fuel injector 68 reduces the number of leaks through the combustion housing by eliminating the spark igniter introduced in some combustion designs. Additionally, concern for thermal expansion from combustor to combustor, particularly for transition duct and / or transition nozzle configurations, is minimized.
The invention in one aspect may be summarized as follows: A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid supply passage extends at least partially through the main body. An axially extending inner body extends inside the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid supply channel. A retractable igniter extends straight from the inner chamber to the outside when the fluid supply channel is applied.
10 gas turbine 12 inlet section 14 working fluid 16 compressor 18 compressed working fluid 20 fuel delivery system 22 combustion chamber 24 combustion gases 26 turbine 28 shaft 30 generator / engine 32 exhaust 34 outlet section 36 exhaust stack 38 not used 40 housing 42 end cap 44 primary fuel nozzle 46 inner surface 48 cap assembly 50 liner 51 inlet 52 hot gas path 54 first combustion zone 56 annular sleeve 58 cooling flow path 60 cooling holes 62 secondary fuel nozzle / fuel injector 64 fluid coupling 66 flow control valve 68 fuel injector 70 retractable igniter 72 main body 74 upstream end 76 downstream end 78 flow path 80 fuel supply line 82 fuel injection ports 84 inner body 86 upstream end 88 downstream end 90 inner chamber 92 opening

权利要求:
Claims (9)
[1]
A fuel injector (68) for a combustor (22) of a gas turbine (10), comprising: a) an annular main body (72) at least partially defining a flow path (78) through the fuel injector (68); b) a Fluidzuführkanal (94), which extends outside the flow path (78) at least partially through the main body (72) and can be acted upon with fluid; c) an axially extending inner body (84) extending inside the main body (72); d) an inner chamber (90) defined at least partially inside the inner body (84), the inner chamber (90) being in fluid communication with the fluid supply channel (94); and e) a retractable igniter (70) extending straight from the inner chamber (90) outwardly into the flow path (78) when the fluid supply channel (94) is fluidized.
[2]
The fuel injector (68) of claim 1, further comprising a spring (106) disposed within the interior chamber (90), the spring (106) coupled to the ignitor (70).
[3]
3. The fuel injector (68) according to claim 1 or 2, further comprising a radially extending pressure plate (110) disposed inside the inner chamber (90), wherein the pressure plate (110) is disposed on the igniter (70) and surrounds the igniter (70) at least partially in the circumferential direction.
[4]
The fuel injector (68) of any one of the preceding claims, wherein the upstream end (86) of the inner body (84) is dome shaped.
[5]
The fuel injector (68) of any one of the preceding claims, further comprising an annular flow path defined at least in part between the main body (72) and the inner body (84).
[6]
The fuel injector (68) of claim 5, further comprising a fuel supply line (80) and at least one fuel injection port (82), the at least one fuel injection port (82) providing fluid communication between the fuel supply line (80) and the annular flow path of the fuel injector (68 ) Are defined.
[7]
The fuel injector (68) of any one of the preceding claims, wherein the main body (72) includes an upstream end (74) and a downstream end (76), the igniter (70) extending downstream from the downstream end (76 ) of the main body (72) when fluid supply passage (94) is pressurized.
[8]
A combustor (22) for a gas turbine (10) comprising: a) an end cover (42) connected to a housing (40), a fuel nozzle (44) extending downstream from the end cover (42) a cap assembly (48) at least partially surrounding a portion of the fuel nozzle (44) and an annular liner (50) extending downstream from the cap assembly (48); and b) a fuel injector (68) extending radially through the liner (50), the fuel injector (68) comprising: i) an annular main body (72) at least partially defining a flow path (78) through the fuel injector (68 ), the main body (72) having a downstream end (76); ii) a fluid supply passage (94) extending at least partially outside the flow path (78) through the main body (72) and being fluidizable; iii) an inner body (84) disposed within the flow path (78) of the main body (72), the inner body (84) having an opening (92) at a downstream end (88) of the inner body (84) ; iv) an inner chamber (90) defined at least partially inside the inner body (84), the inner chamber (90) being in fluid communication with the fluid supply channel (94); v) a retractable igniter (70) disposed inside the inner chamber (90), the igniter (70) extending straight through the opening (92) of the inner body (84) and at least partially into the flow path (78 ) of the main body when the fluid supply passage (94) is charged with fluid.
[9]
A gas turbine (10) comprising: a) a compressor section (16); b) a combustion section downstream of the compressor section (16), the combustion section including a combustion chamber (22), the combustion chamber (22) having at least one annular liner (50) at least partially defining a hot gas path (52) through the combustion chamber (22 ) Are defined; c) a turbine section (26) downstream of the combustion section; and d) a fuel injector (68) extending at least partially through the liner (50) of the combustor (22), the fuel injector (68) comprising: i) an annular main body (72) at least partially defining a flow path (78 defined by the fuel injector (68); ii) a fluid supply passage (94) extending at least partially outside the flow path (78) through the main body (72) and being fluidizable; iii) an axially extending inner body (84) extending inside the main body (72); iv) an inner chamber (90) defined at least partially inside the inner body (84), the inner chamber (90) being in fluid communication with the fluid supply channel (94); and v) a retractable igniter (70) which moves linearly outwardly from the inner chamber (90) into the flow path (78) of the main body (72) toward the hot gas path (52) when the fluid supply channel (94) is acted upon with fluid.

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JP2014238253A|2014-12-18|

引用文献:

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RU2755240C2|2017-12-26|2021-09-14|Ансальдо Энергия Свитзерленд Аг|Burner for combustion chamber of gas turbine power plant, combustion chamber of gas turbine power plant containing such burner, and gas turbine power plant containing such combustion chamber|

法律状态:
2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |

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2018-07-31| PL| Patent ceased|

优先权:

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申请号 | 申请日 | 专利标题

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US13/734,165|US9021781B2|2013-01-04|2013-01-04|Fuel injector having an ignitor for igniting a combustor of a gas turbine|

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