• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a turbine diffuser (188). The turbine diffuser (188) includes an axial diffuser section (202) including a diverging first duct section (212) having an axial flow path (214) along a centerline (208) of the gas turbine diffuser (188). The gas turbine diffuser (188) further includes an axial-radial diffuser section (204) coupled to the axial diffuser section (202), the axial-radial diffuser section (204) having a divergent second conduit section (230) with a curved flow path (232). along the center line (208) from the axial flow path (214) to the radial flow path (234), and the axial-radial diffuser section (204) excludes any turning vanes in the second line section (230).
    公开号:CH703553B1
    申请号:CH01286/11
    申请日:2011-08-02
    公开日:2016-02-29
    发明作者:Deepesh D Nanda；Robit Pruthi；Asif Iqbal Ansari
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background to the invention
    The invention disclosed herein relates to turbine diffusers for use in gas and steam turbines.
    Power plants often include turbines, e.g. Gas turbines. The gas turbine combustes a fuel to produce hot combustion gases that flow through a turbine to drive a load and / or a compressor. The exhaust gases exit the turbine at high speeds and temperatures and into an exhaust or turbine diffuser. The turbine diffuser may be an axial-radial turbine diffuser that directs the flow from an axial direction to a radial direction. Axial-radial turbine diffusers include internal structural elements such as struts and turning vanes. The inner struts hold the walls of the diffuser together tightly and transfer loads from a rotor to a foundation. The internal vanes serve to redirect the flow from the axial to the radial direction. Unfortunately, the design of the turbine diffuser leads to considerable pressure losses, in particular at the inner struts and turning vanes.
    Object of the present invention is therefore to provide an improved turbine diffuser for a fluid flow system with a turbine, in particular for a gas turbine plant, which is capable of redirecting the exiting the turbine fluid flow from an axial direction in a radial direction without significant pressure losses.
    Brief description of the invention
    This object is achieved by a turbine diffuser according to claim 1. Advantageous embodiments of the invention are the subject of the dependent claims.
    Brief description of the drawings
    Features, aspects and advantages of the present invention will be better understood when the following detailed description is read with reference to the accompanying drawings, in which the corresponding parts are represented by numbers in the drawings, wherein:<Tb> FIG. Figure 1 is a cross-section of one embodiment of a gas turbine plant taken along the longitudinal axis;<Tb> FIG. FIG. 2 is a cross-section of one embodiment of a turbine diffuser of the gas turbine of FIG. 1 according to one embodiment; FIG. and<Tb> FIG. FIG. 3 <SEP> is a perspective view of the turbine diffuser of the gas turbine of FIG. 1. FIG.
    Detailed description of the invention
    Specific embodiments of the present invention will be described below.
    In introducing elements of the various embodiments of the present invention, the articles "a," "an," "the," and "the word" (r / s) "are intended to indicate that there are one or more of the elements. The terms "include" and "comprise" are intended to mean that there may be additional elements other than the named elements.
    [0008] The embodiment described below relates to a turbine diffuser shaped to provide a uniform flow path for the passage of the flow from an axial rotational axis relative to the turbine rotational axis to a radial direction without deflecting vanes, while maximizing pressure recovery in the diffuser. As described below, the turbine diffuser according to the present embodiment includes an axial diffuser section, an axial-radial diffuser section, and a radial diffuser section. The axial diffuser section includes diverging walls having one or more struts to reduce pressure losses around the struts and to transition gradually into the axial-radial diffuser section. The axial-radial diffuser section includes a vane-less channel having a large radius of curvature to reduce flow pitches and pressure losses. The axial-radial diffuser section gradually diverts the exhaust flow without abrupt changes between the axial and radial directions, eliminating the need for internal vanes. Instead of a sharp curve or a small radius of curvature, the axial-radial diffuser section has a large radius of curvature along radially inwardly and outwardly directed walls. The radius of curvature may be at least about 1 to 100 times the cross-sectional width of the curved channel along the radius of curvature. For example, the radius of curvature may be greater than or about the same as the one and a half, 2, 3, 4, 5, 6, 7, 8, 9, or 10 times the cross sectional width of the arcuate channel along the radius of curvature. In addition, the described flow-improving turbine diffuser eliminates mechanical problems such as cracks that may occur on vanes.
    FIG. 1 is a cross-section of one embodiment of a gas turbine 118 taken along the longitudinal axis 158. Turbine diffusers without vanes may be used in any type of fluid power system including rotary machines such as gas and steam turbines and are not limited to any particular machine or plant , As will be described below, the turbine diffuser may be deployed within the gas turbine 118 to maximize diffuser performance by providing a uniform flow path for transferring the flow through the diffuser from an axial to a radial direction with respect to the turbine axis of rotation. For example, the turbine diffuser near the inlet port of the diffuser may have an orifice angle to facilitate early flow diffusion and to reduce pressure losses around one or more internal struts and to make the flowpath from axial to radial less abrupt and more profiled , In addition, the diffuser may include certain portions which extend stepwise along the flow path to further enhance the passage of the flow from an axial to a radial flow direction so as to improve the aerodynamics of the diffuser while at the same time reducing possible power loss (eg Turning vanes) is eliminated.
    The gas turbine 118 includes one or more fuel nozzles 160 located in a burner section 162. In certain embodiments, the gas turbine 118 within the burner section 162 may include a plurality of annular combustion chambers 120. Further, each combustor 120 may include a plurality of fuel nozzles 160 annularly or otherwise attached at or near the top end of each combustor 120.
    The air enters through an air inlet section 163 and is compressed by a compressor 132. The compressed air from the compressor 132 is then directed into the burner section 162, where the compressed air is mixed with the fuel. The mixture of compressed air and fuel is typically combusted within the burner section 162 to produce high temperature and high pressure combustion gases used to generate the torque within the turbine section 130. As noted above, multiple combustors 120 may be disposed annularly within burner section 162. Each combustor 120 includes an intermediate piece 172 which directs the hot combustion gases from the combustor 120 into the turbine section 130. In particular, each spacer 172 typically defines a flow of hot gas from the combustor 120 to the nozzle assembly of the turbine section 130 contained within a first stage 174 of the turbine 130.
    As shown, the turbine section 130 includes three separate stages 174, 176, and 178. Each stage 174, 176, and 178 includes a plurality of blades 180 coupled to a rotor wheel 182, which in turn is rotatably mounted to a shaft 184 , Each stage 174, 176, and 178 further includes a nozzle assembly 186 disposed immediately in front of each blade set 180. The nozzle assemblies 186 direct the hot combustion gases to the vanes 180 where the hot combustion gases impart drive forces to the vanes that cause the vanes 180 to rotate, thereby also rotating the shaft 184. The hot combustion gases flow through each of the stages 174, 176, and 178 and generate motive forces on the blades 180 within each of the stages 174, 176, and 178. The hot combustion gases then exit the gas turbine 130 through a turbine diffuser 188. The turbine diffuser 188 operates by moving the turbine Speed of the fluid flow through the turbine diffuser 188 reduced and the static pressure is increased simultaneously. The turbine diffuser includes a strut 190 disposed between the walls of the turbine diffuser 188. The strut 190 holds the walls together. The number of struts 190 varies and may be between 1 and 10 or more. The turbine diffuser 188 includes a flared shape for communicating the fluid flow without internal vanes from an axial to a radial direction while providing an opening angle proximate the inlet port 192 of the turbine diffuser 188 to allow early flow diffusion.
    FIG. 2 is a cross-sectional side view of the turbine diffuser 188 of FIG. 1 detailing the angles near the inlet port 192 and the expanding shape of the turbine diffuser 188. The turbine diffuser includes an axial diffuser section 202, an axial-radial diffuser section 204, and a radial diffuser section 206. A geometric centerline 208 of the turbine diffuser, which typically defines the flow path, extends from the inlet port 192 of the turbine diffuser 188 toward an exhaust port 210 The cross-sectional area of the turbine diffuser 188 increases downstream along the flow path from the inlet port 192 to the outlet port 210.
    The axial diffuser section 202 is formed by a first conduit section 212 that includes an axial flow path 214 along the centerline 208 of the turbine diffuser 188. The first conduit section 212 includes a first wall 216 spaced from the second wall 218. Furthermore, the first wall 216 and the second wall 218 are oppositely disposed about the axial flow path 214. The first wall 216 is located closer in radial direction relative to the axis of rotation of the turbine 130, indicated by the dashed line 220, than the second wall 218. The first wall 216 extends along the axial flow path 214 at a first angle 222 relative to the axis of rotation 220 the turbine 130. In certain embodiments, the first angle 222 may be a negative angle that ranges between about 0-8 degrees, preferably between 2-6 degrees, or more preferably between 4-5 degrees. For example, the first angle 222 may be equal to about 2, 4, 6, or 8 degrees or any angle therebetween. The second wall 218 extends along the axial flow path 214 at a second angle 226 relative to the axis of rotation 220. In certain embodiments, the second angle 226 may be a positive angle that is between about 16-20 degrees, or preferably between 17-19 degrees emotional. For example, the second angle 226 may be equal to about 16, 17, 18, 19, or 20 degrees or any angle therebetween. In the illustrated embodiment, the first angle 222 and the second angle 226 are not 0 degrees. In some embodiments, the first angle 222 is less than or about 8 degrees, and the second angle 226 is greater than or about 16 degrees.
    Due to the first and second angles 222 and 226, the first wall 216 and the second wall 218 diverge along the axial flow path 214, respectively. As a result of the divergence of the first wall 216 and the second wall 218, the first conduit portion 212, as shown in FIG. 2, includes a first cross-sectional area 228 (ie, perpendicular to the centerline 208) extending along the axial flow path 214 between the first walls 216 and the second wall 218 enlarged. The expansion of the cross-sectional area 228 across the flow path may cause premature flow diffusion that reduces pressure losses around the strut 190. Furthermore, this expansion results in a uniform flow path transition from the axial to the radial direction, as will be described below.
    The axial diffuser section 202 is coupled to the axial-radial diffuser section 204. The axial-radial diffuser section 204 directs the flow from the axial diffuser section 202 to the radial diffuser section 206. The axial-radial diffuser section 204 is formed by a second conduit section 230 that includes a curved flow path 232 along the centerline 208 from the axial flowpath 214 to the radial flowpath 234 , The second conduit section 230 includes a first curved wall 236 spaced from a second curved wall 238. Furthermore, the first curved wall 236 and the second curved wall 238 are disposed opposite to each other around the curved flow path 232. The first curved wall 236 is mounted facing the axis of rotation 220 of the turbine 130, while the second curved wall 238 is located more distal relative to the axis of rotation 220. The first wall 216 and the second wall 218 of the first conduit portion 212 having the first and second angles 222 and 226 respectively extend toward the first and second curved walls 236 and 238 of the second conduit portion 230. In some embodiments, the first wall may be 216 and the second wall 218 of the first conduit section 212 having the first and second angles 222 and 226 respectively extend directly to the first and second curved walls 236 and 238. The expansion down to the curved walls 236 and 238 makes the flow path transfer from the axial diffuser section 202 to the axially-radial diffuser section 204 more aerodynamic, thereby reducing pressure losses, which are typically associated with sharp cross-overs in the direction of the flowpath.
    The first curved wall 236 extends along the curved flow path 232 with a first radius of curvature 240, while the second curved wall 238 extends along the curved flow path 232 with a second radius of curvature 242. The mean of these radii 240 and 242 corresponds to the radius of curvature 243 of the centerline 208 along the curved flowpath 232. In certain embodiments, the radii of curvature 240, 242, and 243 may vary along the longitudinal extent of the first curved wall 236 and the second curved wall 238. Accordingly, the centers 241 of the radii 240, 242, and 243 may shift to increase or decrease the radii 240, 242, and 243. At certain points along the length of the second conduit section 230, the first radius of curvature 240 may differ from the second radius of curvature 242, while the first radius of curvature 240 and the second radius of curvature 242 may be the same at other locations. Alternatively, the first radius of curvature 240 and the second radius of curvature 242 may differ along the entire longitudinal extent of the first curved wall 236 and the second curved wall 238. In certain embodiments, the difference between the first radius of curvature 240 and the second radius of curvature 242 may be between 0 and about 50 percent, preferably between 10 and 40 percent, or more preferably between 20 and 30 percent. For example, the difference may be about 15, 20, 25, 30, or 35 percent, or any percentage in between. In certain embodiments, the first radius of curvature 240 may be greater than the second radius of curvature 242. In alternative embodiments, the second radius of curvature 242 may be greater than the first radius of curvature 240. In other embodiments, the first radius of curvature 240 and the second radius of curvature 242 may be equal.
    In certain embodiments, the first radius of curvature 240 may be approximately in the range of 30 to 390 centimeters, 80 to 340 centimeters, 130 to 390 centimeters, 180 to 300 centimeters, or 220 to 260 centimeters. For example, the first radius of curvature 240 may be about 30, 40, 50, 60, 70, 80, 90, or 100 centimeters, or any distance therebetween. In certain embodiments, the first radius of curvature 240 may be at least greater than or about 100 centimeters. In certain embodiments, the second radius of curvature 242 may be in the range of about 30 to 510 centimeters, 80 to 460 centimeters, 130 to 410 centimeters, 180 to 360 centimeters, or 230 to 310 centimeters. For example, the second radius of curvature 242 may be about 30, 40, 50, 60, 70, 80, 90, or 100 centimeters, or any distance therebetween. In certain embodiments, the first radius of curvature 240 may be at least greater than or about 100 centimeters. In certain embodiments, the radius 243 of the curved flowpath 232 may be in the range of about 30 to 450 centimeters, 80 to 400 centimeters, 130 to 350 centimeters, 180 to 300 centimeters, or 220 to 260 centimeters. For example, radius 243 may be about 30, 40, 50, 60, 70, 80, 90, or 100 centimeters or any distance therebetween. In certain embodiments, the radius 243 may be at least greater than or about 30 centimeters. In certain embodiments, the radius 243 may be at least greater than or about 100 centimeters.
    The curvature of the walls 236 and 238 allows for a smoother, more aerodynamic flow path transition, eliminating the need for an internal turning vane in the second conduit section 230. Thus, the axial-radial diffuser portion 204 is formed without any internal vanes. Preferably, the first and second curved walls 236 and 238 diverge, respectively, along the curved flow path 232 to allow for greater diffusion during the transition from the axial to the radial direction. In this preferred embodiment, the curved second conduit section has a second cross-sectional area 244 (i.e., perpendicular to the centerline 208) that increases along the curved flowpath 232 between the first wall 236 and the second wall 238. In other words, the cross-sectional area 244 has a cross-sectional width 246 along the average radius of curvature that increases along the curved flow path 232. The expansion of the cross-sectional width 246 within the axial-radial diffuser section 204 increases the diffusion of the flow and simultaneously diverts the flow from an axial to a radial direction.
    In certain embodiments, the radii 240, 242, and 243 may be at least about 1-100, 1-50, 1-25, or 1-10 times the cross-sectional width 246 of the curved flow path 232 along the average radius of curvature. For example, the radii 240, 242, and 243 may be greater than or about the same size as the one and a half, 2, 3, 4, 5, 6, 7, 8, 9, or 10 times the cross sectional width 246.
    From the axial-radial diffuser section 204, the flow is directed to the radial diffuser section 206. The axial-radial diffuser section 204 is coupled to the radial diffuser section 206. The radial diffuser section 206 is formed by a third conduit section 248 that includes a radial flow path 234 along the centerline 208 of the diffuser 188. The third line section 248 includes a first transverse to the turbine rotational axis 220 extending wall 250, which is spaced from a second transverse to the turbine rotational axis 220 extending wall 252. Furthermore, the first wall 250 extending transversely to the turbine rotational axis 220 and the second transverse wall 252 extending transverse to the turbine rotational axis 220 are arranged opposite to each other about the radial flow path 234; in the present embodiment, diverging first and second curved walls 236 and 238 of the second conduit section 230 extend as far as the first transverse to the turbine rotational axis 220 extending wall 250 and second transverse to the turbine rotational axis 220 extending wall 252. The first transverse to the turbine rotational axis 220 extending wall 250 diverges in the present embodiment of the second transverse to the turbine rotational axis 220 extending wall 252 along the radial flow path 234. Consequently, the third conduit portion 248 has a third cross-sectional area 254 (ie, perpendicular to centerline 208) extending along the radial flowpath 234 between the first transverse wall 250 to the turbine rotational axis 220 and the second transverse to the turbine rotational axis 220 extending wall 252 extends to increase the diffusion and the diffusion performance. From the radial diffuser section 206, the flow is directed to the outlet 210 of the turbine diffuser 188.
    FIG. 3 is a perspective view of the turbine diffuser 188 illustrating the contours and extent of the diffuser 188. FIG. The turbine diffuser 188 includes the axial diffuser section 202, the axial-radial diffuser section 204, and the radial diffuser section 206, as described above. The axial diffuser section 202 includes the first and second walls 216 and 218. The axial-radial diffuser section 204 includes the first and second curved walls 236 and 238. Both the first and second walls 216 and 218 and at least portions of the first and second curved walls 236 and 238 include a circular segment-shaped curvature in the circumferential direction, as indicated by arrow 262, with respect to the turbine rotational axis 220. The circular segment curvature of the walls 216, 218, 236, and 238 permits annular arrangement of the turbine diffuser 188 about the turbine exit 130. In some embodiments, For example, one or more turbine diffusers 188 may be distributed around the turbine exhaust 130. As depicted in FIG. 3, the turbine diffuser 188 includes a third wall 264 and a fourth wall 266 that follow the flow path 214, 232, 234, 268, typically defined by the centerline 208. The third wall 264 and the fourth wall 266 are disposed opposite each other and are located between the first wall 216 and the second wall 218, the first curved wall 236 and the second curved wall 238 and the first transverse to the turbine rotating axis 220 extending wall 250 and The third wall 264 and the fourth wall 266 diverge from the inlet port 192 in the flow direction 268 through the diffuser to the outlet port 210. The cross-sectional area of the turbine diffuser 188 (ie, perpendicular to the centerline 208) ) extends downstream from the inlet port 192 to the outlet port 210 of the diffuser 188 both in the dimension of the turbine diffuser indicated by the arrow 270 and in the dimension 272 of the turbine diffuser indicated by the arrow 272.
    In certain embodiments, the radius of curvature 243 of the geometric centerline may be at least about 30 centimeters and / or 1-10 times the cross-sectional width 246 along the mean radius of curvature 243. In other embodiments, the radius of curvature 243 may be at least about twice the cross-sectional width 246 along the mean radius of curvature 243.
    Overall, the aerodynamic design of the diffuser 188 improves diffuser performance while eliminating potential power loss and mechanical problems (i.e., vaned vanes).
    The invention relates to a turbine diffuser 188. The turbine diffuser 188 includes an axial diffuser section 202 including a first diverging duct section 212 having an axial flow path 214 along a centerline 208 of the gas turbine diffuser 188. The gas turbine diffuser 188 also includes an axial-radial diffuser section 204 is coupled to the axial diffuser section 202, wherein the axial-radial diffuser section 204 includes a second divergent conduit section 230 with a curved flow path 232 along the centerline 208 of the axial flow path 214 to the radial flow path 234, and the axial-radial diffuser section 204 includes any diverting vanes in the second Excludes line section 230.
    LIST OF REFERENCE NUMBERS
    [0026]<Tb> 118 <September> Gas Turbine<Tb> 120 <September> combustion chamber<Tb> 130 <September> Turbine<Tb> 132 <September> Compressor<Tb> 158 <September> longitudinal axis<Tb> 160 <September> fuel nozzles<Tb> 162 <September> combustor section<Tb> 163 <September> air intake portion<Tb> 172 <September> Transfer guide<Tb> 174 <September> Level<Tb> 176 <September> Level<Tb> 178 <September> Level<Tb> 180 <September> blades<Tb> 182 <September> rotor wheel<Tb> 184 <September> wave<Tb> 186 <September> nozzle arrangements<Tb> 188 <September> turbine diffuser<Tb> 190 <September> strut<Tb> 192 <September> inlet<tb> 202 <SEP> Axial diffuser section<tb> 204 <SEP> Axial-radial diffuser section<tb> 206 <SEP> Radial diffuser section<Tb> 208 <September> centerline<Tb> 210 <September> outlet<tb> 212 <SEP> First line section<tb> 214 <SEP> Axial flow path<tb> 216 <SEP> First wall<tb> 218 <SEP> Second wall<Tb> 220 <September> longitudinal axis<tb> 222 <SEP> First angle<tb> 226 <SEP> Second angle<tb> 228 <SEP> First cross-sectional area<tb> 230 <SEP> Second line section<tb> 232 <SEP> Curved flow path<tb> 234 <SEP> Radial flow path<tb> 236 <SEP> First curved wall<tb> 238 <SEP> Second curved wall<tb> 240 <SEP> First radius of curvature<Tb> 241 <September> center<tb> 242 <SEP> Second radius of curvature<tb> 243 <SEP> Average radius of curvature<tb> 244 <SEP> Second cross-sectional area<Tb> 246 <September> section width<tb> 248 <SEP> Third line section<tb> 250 <SEP> First vertical wall<tb> 252 <SEP> Second vertical wall<tb> 254 <SEP> Third cross-sectional area<Tb> 262 <September> Arrow<tb> 264 <SEP> Third wall<tb> 266 <SEP> Fourth wall<tb> 268 <SEP> Downstream Direction<tb> 270 <SEP> Vertical dimension<tb> 272 <SEP> Horizontal dimension
    权利要求:
    Claims (10)
    [1]
    A turbine diffuser (188) for a fluid power plant having a turbine (130), particularly for a gas turbine plant (118), for redirecting fluid flow exiting the turbine from an axial flow path (214) relative to a turbine rotational axis (220) with respect to the turbine rotational axis (220) radial flow path (234), wherein the turbine diffuser (188) comprises:an axial diffuser section (202) formed by a first conduit section (212) comprising the axial flow path (214) along a geometric centerline (208) of the turbine diffuser (188), the first conduit section (212) having a first cross-sectional area (212); 228) perpendicular to the geometric centerline (208) which increases along the axial flow path (214); andan axial-radial diffuser section (204) coupled to the axial diffuser section (202) and formed by a second conduit section (230) having a curved flow path (232) along the geometric centerline (208) from the axial flow path (214) radial flow path (234), wherein the second conduit portion (230) has a second cross-sectional area (244) perpendicular to the geometric centerline (208) that increases along the curved flowpath (232), the geometric centerline (208) being along the curved Flow path (232) has a radius of curvature (243) of at least 30 centimeters and the axial-radial diffuser portion (204) in the second line section (230) is free of any turning vanes.
    [2]
    The turbine diffuser of claim 1, wherein the turbine diffuser (188) includes a radial diffuser section (206) coupled to the axial-radial diffuser section (204) and formed by a third conduit section (248) defining the radial flow path (234 ) along the geometric centerline (208), the third conduit portion (248) having a third cross-sectional area (254) perpendicular to the geometric centerline (208) that increases along the radial flowpath (234).
    [3]
    The turbine diffuser of claim 1, wherein the radius of curvature (243) of the geometric centerline (208) along the curved flowpath (232) is at least 100 centimeters.
    [4]
    The turbine diffuser of claim 1, wherein the second conduit section (230) includes a first curved wall (236) and a second curved wall (238) spaced therefrom, the first curved wall (236) being along the curved flow path (232) first radius of curvature (240) and the second curved wall (238) extend along the curved flow path (232) with a second radius of curvature (242).
    [5]
    5. The turbine diffuser of claim 4, wherein when using the turbine diffuser in a fluid power plant having a turbine (130), the first curved wall (236) is located closer to the turbine rotation axis (220) in radial direction with respect to the turbine rotation axis (220) than the second curved one Wall (238).
    [6]
    6. The turbine diffuser of claim 4, wherein the first radius of curvature (240) of the first curved wall (236) and the second radius of curvature (242) of the second curved wall (238) are equal.
    [7]
    7. The turbine diffuser of claim 4, wherein the first radius of curvature (240) of the first curved wall (236) and the second radius of curvature (242) of the second curved wall (238) differ.
    [8]
    The turbine diffuser of claim 4, wherein the first curved wall (236) and the second curved wall (238) diverge along the curved flow path (232).
    [9]
    The turbine diffuser of claim 1, wherein the first conduit section (212) comprises a first wall (216) and a second wall (218) spaced therefrom, wherein when using the turbine diffuser in a fluid flow system having a turbine (130), the first wall (216 ) is disposed closer to the turbine rotational axis (220) in radial direction with respect to the turbine rotational axis (220) than the second wall (218), and wherein the first wall (216) and the second wall (218) are spaced from one another along the axial flow path (214) diverge.
    [10]
    10. The turbine diffuser of claim 9, wherein when using the turbine diffuser in a fluid power plant having a turbine, the first wall extends along the axial flow path at a first angle relative to the turbine axis of rotation. the second wall (218) extends along the axial flow path (214) at a second angle (226) relative to the turbine rotation axis (220) and the first (222) and second angles (226) are not 0 degrees.
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    同族专利:
    公开号 | 公开日
    CN102374030A|2012-03-14|
    CN102374030B|2016-06-01|
    DE102011052236A1|2012-02-09|
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    US20120034064A1|2012-02-09|
    JP2012036891A|2012-02-23|
    JP6059424B2|2017-01-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    CH484358A|1968-02-15|1970-01-15|Escher Wyss Ag|Exhaust housing of an axial turbo machine|
    US4182595A|1978-01-30|1980-01-08|Westinghouse Electric Corp.|Discharge assembly for an axial flow compressor|
    JPS5965907U|1982-10-25|1984-05-02|
    US5188510A|1990-11-21|1993-02-23|Thomas R. Norris|Method and apparatus for enhancing gas turbo machinery flow|
    EP0581978B1|1992-08-03|1996-01-03|Asea Brown Boveri Ag|Multi-zone diffuser for turbomachine|
    DE4422700A1|1994-06-29|1996-01-04|Abb Management Ag|Diffuser for turbomachinery|
    WO1996004409A1|1994-08-01|1996-02-15|Franz Hehmann|Selected processing for non-equilibrium light alloys and products|
    GB9415685D0|1994-08-03|1994-09-28|Rolls Royce Plc|A gas turbine engine and a diffuser therefor|
    US5603605A|1996-04-01|1997-02-18|Fonda-Bonardi; G.|Diffuser|
    JP4114253B2|1998-11-30|2008-07-09|株式会社Ｉｈｉ|Gas turbine exhaust casing|
    US6488470B1|1999-08-03|2002-12-03|Jerzy A. Owczarek|Annular flow diffusers for gas turbines|
    DE10037684A1|2000-07-31|2002-02-14|Alstom Power Nv|Low pressure steam turbine with multi-channel diffuser|
    US6802690B2|2001-05-30|2004-10-12|M & I Heat Transfer Products, Ltd.|Outlet silencer structures for turbine|
    WO2004106717A2|2003-05-28|2004-12-09|Combustion Science & Engineering, Inc.|Method and apparatus for reducing total pressure loss in a turbine engine|
    GB2475448B8|2005-08-04|2015-12-16|Rolls Royce Power Eng|Gas turbine exhaust diffuser|
    US8439633B2|2010-01-04|2013-05-14|General Electric Company|Hollow steam guide diffuser having increased pressure recovery|US20130022444A1|2011-07-19|2013-01-24|Sudhakar Neeli|Low pressure turbine exhaust diffuser with turbulators|
    CN103016079B|2012-11-28|2015-12-02|东方电气集团东方汽轮机有限公司|Exhaust steam cylinder of low-power steam turbine|
    US9644496B2|2013-03-13|2017-05-09|General Electric Company|Radial diffuser exhaust system|
    US9476324B2|2013-09-19|2016-10-25|Solar Turbines Incorporated|Exhaust collector with curved side panel|
    JP6507535B2|2014-09-10|2019-05-08|株式会社Ihi|Bypass duct fairing for low bypass ratio turbofan engine and turbofan engine having the same|
    EP3054086B1|2015-02-05|2017-09-13|General Electric Technology GmbH|Steam turbine diffuser configuration|
    EP3334904A1|2015-08-12|2018-06-20|General Electric Company|Diffuser for a turbine engine and method of forming same|
    US10041365B2|2015-11-24|2018-08-07|General Electric Company|System of supporting turbine diffuser|
    US10036283B2|2015-11-24|2018-07-31|General Electric Company|System and method for diffuser AFT plate assembly|
    US10041377B2|2015-11-24|2018-08-07|General Electric Company|System and method for turbine diffuser|
    US10036267B2|2015-11-24|2018-07-31|General Electric Company|System of supporting turbine diffuser outlet|
    US10287920B2|2015-11-24|2019-05-14|General Electric Company|System of supporting turbine diffuser|
    US10563543B2|2016-05-31|2020-02-18|General Electric Company|Exhaust diffuser|
    CN109372637B|2018-12-16|2021-04-16|中国航发沈阳发动机研究所|Flow path design method for gas turbine exhaust device|
    CN109630219B|2018-12-16|2022-03-04|中国航发沈阳发动机研究所|Gas turbine exhaust apparatus|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2018-03-29| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/852,129|US20120034064A1|2010-08-06|2010-08-06|Contoured axial-radial exhaust diffuser|
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