CN102374030B - Curvilinear axially-radially exhaust diffuser - Google Patents
Curvilinear axially-radially exhaust diffuser Download PDFInfo
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- CN102374030B CN102374030B CN201110230203.6A CN201110230203A CN102374030B CN 102374030 B CN102374030 B CN 102374030B CN 201110230203 A CN201110230203 A CN 201110230203A CN 102374030 B CN102374030 B CN 102374030B
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- flow path
- wall
- axially
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- radial
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
Abstract
The present invention relates to curvilinear axially-radially exhaust diffuser, according to an embodiment, a kind of system includes combustion gas turbine bubbler. Combustion gas turbine bubbler includes axially diffusing device section, and this axially diffuses the first conduit portion that device section includes having axial flow path along the centrage of combustion gas turbine bubbler. Combustion gas turbine bubbler also include being connected in axially diffuse in device section axial-radial diffuser section, wherein axially-radial diffuser section includes the second conduit portion, this second conduit portion has the bending flow path leading to radial flow path from axial flow path along centrage, and axially-radial diffuser section does not include any steering blade in the second conduit portion.
Description
Technical field
Subject matter disclosed herein relates to turbine, and more particularly, to the exhaust diffuser for using together with combustion gas turbine and steam turbine.
Background technology
Generating equipment is often in conjunction with turbine, for instance gas-turbine unit. Gas turbine engine combustion fuel is to produce the burning gases of heat, and it flows through turbine to drive load and/or compressor. At a high speed with under high temperature, turbine is left in aerofluxus, and enters exhaust diffuser. Exhaust diffuser can be axial-radial direction exhaust diffuser, and it makes stream be transited into radial direction from axial direction. Axially-radial direction exhaust diffuser combines inner structural features, for instance pillar and steering blade. Inner leg keeps the wall of bubbler with the relation being fixed to one another, and from rotor, load is transferred to base. Internal turn blade contributes to making stream from being axially diverted to radial direction. Unfortunately, exhaust diffuser design result in the great pressure loss, especially at inner leg and steering blade place.
Summary of the invention
Outlined below some embodiment matched with initial claimed invention scope. These embodiments are not limiting as scope of invention required for protection, and these embodiments are merely intended to the brief overview of the possible form providing the present invention on the contrary. It practice, the present invention can comprise various forms that can be similar or different from following embodiment.
According to first embodiment, a kind of system includes combustion gas turbine bubbler. Combustion gas turbine bubbler includes axially diffusing device section, this axially diffuses the first conduit portion that device section includes having axial flow path along the centrage of combustion gas turbine bubbler, and wherein the first conduit portion has axially flow path and the first cross-sectional area of extending. Combustion gas turbine bubbler also include being connected in axially diffuse in device section axial-radial diffuser section, wherein axially-radial diffuser section includes the second conduit portion, this second conduit portion has the bending flow path leading to radial flow path along centrage from axial flow path, second conduit portion has the second cross-sectional area extended along bending flow path, bending flow path has at least above or is equal to the radius of about 30 centimetres, and axially-radial diffuser does not include any steering blade in the second conduit portion.
According to the second embodiment, a kind of system includes combustion gas turbine bubbler. Combustion gas turbine bubbler includes axially diffusing device section, and this axially diffuses the first conduit portion that device section includes having axial flow path along the centrage of combustion gas turbine bubbler. Combustion gas turbine bubbler also include being connected in axially diffuse in device section axial-radial diffuser section, wherein axially-radial diffuser section includes the second conduit portion, second conduit portion has the bending flow path leading to radial flow path from axial flow path along centrage, and axially-radial diffuser section does not include any steering blade in the second conduit portion.
According to the 3rd embodiment, a kind of method includes making the exhaust stream from turbine to carry out axially-radial diffusion by bending conduit along the bending flow path not having any steering blade, and wherein bending flow path has at least above or is equal to the radius of cross-sectional width 2 times of bending conduit.
Accompanying drawing explanation
When reading described further below with reference to accompanying drawing, being better understood with these and further feature, aspect and the advantage of the present invention, wherein similar in all of the figs label represents similar parts, wherein:
Fig. 1 is the cross-sectional view of an embodiment of the gas-turbine unit by longitudinal axis segmentation;
Fig. 2 is the cross-sectional view of an embodiment of the exhaust diffuser of the curve-like (contoured) of the gas-turbine unit of the Fig. 1 according to an embodiment; And
Fig. 3 is the perspective view of an embodiment of the curvilinear exhaust diffuser of the gas-turbine unit of Fig. 1.
Parts list
118 gas-turbine units
120 burners
130 turbines
132 compressors
158 longitudinal axis
160 fuel nozzles
162 combustor section
163 air inlet section
172 changeover portions
174 grades
176 grades
178 grades
180 blades
182 impeller of rotor
184 axles
186 nozzle assemblies
188 exhaust diffusers
190 pillars
192 entrances
202 axially diffuse device section
204 axially-radial diffuser section
206 radial diffuser section
208 centrages
210 outlets
212 first conduit portions
214 axial flow path
216 first walls
218 second walls
220 longitudinal axis
222 first angles
226 second angles
228 first cross-sectional areas
230 second conduit portions
232 bending flow paths
234 radial flow path
236 first curved walls
238 second curved walls
240 first curvature radius
241 centers
242 second curvature radiuss
243 mean radius of curvature
244 second cross-sectional areas
246 cross-sectional width
248 the 3rd conduit portions
250 first vertical walls
252 second vertical walls
254 the 3rd cross-sectional areas
262 arrows
264 the 3rd walls
266 the 4th walls
268 downstream directions
270 vertical dimensions
272 horizontal sizes
Detailed description of the invention
The one or more specific embodiments of the present invention explained below. In order to be devoted to the simple and clear description providing these embodiments, it is likely not to have all features that actual embodiment is fully described in the description. It should be understood that, in the research of this type of actual embodiment any, as in any engineering or design object, the specific decision-making of many embodiments must be made, specific purpose with the Study of the Realization person, such as in accordance with the constraint that system and business are relevant, it is likely to change according to embodiment. Moreover, it is appreciated that this type of research work is probably complicated and consuming time, but for benefiting from those of ordinary skill disclosed by the invention, remains it undertake design, structure and the routine matter manufactured.
When introducing elements of various embodiments of the present invention, word " ", " one ", " being somebody's turn to do " and " described " are intended to indicate one or more element. Word " includes ", " comprising " and " having " be intended to for inclusive and mean except the element listed, it is also possible to have other element.
The disclosed embodiments relate to a kind of curvilinear turbine diffuser, to provide smooth flow path, thus make stream from axial transitions to radial direction when not having steering blade, make the pressure in bubbler recover to maximize simultaneously. As discussed below, disclosed turbine diffuser can include axially diffusing device section, axially-radial diffuser section and radial diffuser section. Axially diffuse device section and include the divergent wall of one or more column circumference, to reduce the pressure loss of column circumference, and be gradually transition to axially-radial diffuser section. Axially-radial diffuser section includes vaneless conduit, and it has big radius of curvature to reduce flow separation and the pressure loss. Such as, axially-radial diffuser section makes exhaust stream gradually turn to when axially and radially not having any unexpected change between direction, thus eliminating the demand for internal turn blade. Axially-radial diffuser section has a big radius of curvature along inner radial wall and outer wall, but not turns to suddenly or little radius of curvature. This radius of curvature can be at least about 1 to 100 times of the cross-sectional width of turbine diffuser. Such as, radius of curvature can more than or equal to about 1.5,2,3,4,5,6,7,8,9 or 10 times of the cross-sectional width of turbine diffuser. It addition, in order to improve mobile performance, disclosed turbine diffuser eliminates the mechanical problem being associated with steering blade, for instance crackle.
Fig. 1 is the cross-sectional side view of an embodiment of the gas-turbine unit 118 along longitudinal axis 158. It should be understood that can be used for including in any fluid flow system of rotary machine without the curvilinear exhaust diffuser of steering blade, for instance gas-turbine unit and steam turbine engines, and it is not intended to be limited to any special machine or system. As described further below, curvilinear exhaust diffuser can be used in gas-turbine unit 118, in order to by providing smooth flow path to make the stream through bubbler from axial transitions to radial direction, thus maximizing bubbler performance. Such as, angle can be set near diffusor entry to provide stream diffusion in advance, thus the pressure loss reduced around one or more inner leg, and make axially to the flow path of radial direction less suddenly and more curve-like. In addition, bubbler can include the part extended gradually along flow path, thus further enhancing the transition from axial to the stream of radial flow direction, thus improving the aerodynamic performance of bubbler, eliminating the source (such as internal turn blade) of performance loss simultaneously.
Gas-turbine unit 118 includes the one or more fuel nozzles 160 being positioned in combustor section 162. In certain embodiments, gas-turbine unit 118 can include multiple burners 120 of being arranged in combustor section 162 with annular array. Additionally, each burner 120 can include multiple fuel nozzle 160, the plurality of fuel nozzle 160 be connected on the head end of each burner 30 with annular array or other arrangement mode or near.
Air is entered by air inlet section 163 and is compressed by compressor 132. Then the compression air of in the future compressor 132 can introduce in combustor section 162, compression air can be made herein to mix mutually with fuel. The mixture of compression air and fuel generally burns in combustor section 162, and to produce High Temperature High Pressure burning gases, this gas can be used for generation moment of torsion in turbine section 130. As noted above, multiple burners 120 can be annularly disposed in combustor section 162. Each burner 120 includes changeover portion 172, and this changeover portion 172 guides the burning gases of heat into turbine section 130 from burner 120. Specifically, each changeover portion 172 generally defines the hot gas path of the nozzle assembly leading to turbine section 130 from burner 120, and it includes in the first order 174 of turbine 130.
As it can be seen, turbine section 130 includes three levels 174,176 and 178 separately. Each level 174,176 and 178 includes the multiple blades 180 being connected on impeller of rotor 182, and impeller of rotor is rotatably connected on axle 184. Each level 174,176 and 178 also includes the nozzle assembly 186 being set directly at each group of blade 180 upstream. Nozzle assembly 186 guides the burning gases of heat into blade 180, and herein, power is applied on blade 180 by the burning gases of heat, so that blade 180 rotates, so that axle 184 rotates. The burning gases of heat flow through each level 174,176 and 178, are applied to by power on the blade 180 in each level 174,176 and 178. Then the burning gases of heat can leave gas turbine section 130 by exhaust diffuser 188. Exhaust diffuser 188 flows through the speed of exhaust diffuser 188 by reducing fluid, also improves static pressure simultaneously and works to reduce the acting of gas-turbine unit 118. Exhaust diffuser includes the pillar 190 being arranged between the wall of exhaust diffuser 188. Pillar 190 is with relation retaining wall fixing relative to each other. The quantity of pillar 190 is variable, and can 1 to 10 or bigger between scope in. Exhaust diffuser 188 includes curve shape, so that fluid flows to radial direction when not having any internal turn blade from axial direction, also includes angle to allow stream diffusion in advance near the entrance 192 of exhaust diffuser 188 simultaneously.
Fig. 2 is the cross-sectional side view of Fig. 1 exhaust diffuser 188, and it show further the angle near entrance 192 and the curve shape of exhaust diffuser 188. Exhaust diffuser 188 includes axially diffusing device section 202, axially-radial diffuser section 204 and radial diffuser section 206. Centrage 208 substantially limits from the entrance 192 of exhaust diffuser 188 towards the flow path of outlet 210 extension. In a word, the cross-sectional area of exhaust diffuser 188 downstream extends towards outlet 210 along flow path from entrance 192.
Axially diffusing device section 202 and include the first conduit portion 212, this first conduit portion 212 has axial flow path 214 along the centrage 208 of exhaust diffuser 188. First conduit portion 212 includes the first wall 216 of deviation the second wall 218. Additionally, the first wall 216 and the second wall 218 are arranged to about axial flow path 214 relative to each other. First wall 216 be mounted to relative to the rotation axis of the turbine 130 indicated by dotted line 220 closer to or close, and the second wall 218 is farther relative to rotation axis 220. First wall 216 axially flow path 214 extends with the first angle 222 relative to the rotation axis 220 of turbine 130. In certain embodiments, the first angle 222 can be scope negative angle between about 0-8 degree, 2-6 degree or 4-5 degree. Such as, the first angle 222 can at least equal to or more than about 2,4,6 or 8 degree, or any angle between. It addition, the second wall 218 axially flow path 214 extends with the second angle 226 relative to rotation axis 220. In certain embodiments, the second angle 226 can be scope positive angle between about 16-20 degree or 17-19 degree. Such as, the second angle 226 can at least equal to or more than about 16,17,18,19 or 20 degree, or any angle between. In an illustrated embodiment, the first angle 222 and the second angle 226 are not 0 degree. In certain embodiments, the first angle 222 is less than or equal to about 8 degree, and the second angle 226 is more than or equal to about 16 degree.
First wall 216 and the second wall 218 respectively due to the first angle 222 and the second angle 226 axially flow path 214 and diverging from one another open. Due to dispersing of the first wall 216 and the second wall 218, (namely first conduit portion 212 includes the first cross-sectional area 228 as shown in Figure 2, it is perpendicular to centrage 208), this first cross-sectional area 228 axially flow path 214 extends between the first wall 216 and the second wall 218. Cross-sectional area 228 crosses over the extension of flow path can provide stream diffusion in advance, which reduces the pressure loss of the bubbler aspect of performance crossing over pillar 190. Additionally, as described below, this extension makes from axially to the flow path transitions smooth of radial direction.
Axially diffuse device section 202 to be connected on axially-radial diffuser section 204. Axially-radial diffuser section 204 makes stream transit to radial diffuser section 206 from axially diffusing device section 202. Axially-radial diffuser section 204 includes the second conduit portion 230, and this second conduit portion 230 has the bending flow path 232 leading to radial flow path 234 from axial flow path 214 along centrage 208. Second conduit portion 230 includes the first curved wall 236 of deviation the second curved wall 238. Additionally, the first curved wall 236 and the second curved wall 238 are arranged to about bending flow path 232 relative to each other. First curved wall 236 be mounted to relative to the rotation axis 220 of turbine 130 closer to or close, and the second curved wall 238 is farther relative to rotation axis 220. First angle 222 and the second angle 226 extend towards the first curved wall 236 and the second curved wall 238 respectively. It practice, in certain embodiments, the first angle 222 and the second angle 226 can extend directly to the first curved wall 236 and the second curved wall 238 respectively. The extension of the angle 222 and 226 of local inclination wall 236 and 238 makes more to meet aerodynamic from axially diffusing device section 202 to the flow path transition axially diffusing device section 204, thus decrease the pressure loss generally associated with the unexpected transitional face in flow path direction at bubbler aspect of performance.
First curved wall 236 bends along bending flow path 232 with first curvature radius 240, and the second curved wall 238 bends along bending flow path 232 with second curvature radius 242. The meansigma methods of these radiuses 240 and 242 can be limited relative to the mean radius of curvature 243 of centrage 208 by along bending flow path 232. In certain embodiments, radius of curvature 240,242 and 243 can change along the length of the first curved wall 236 and the second curved wall 238. Therefore, the center 241 of radius 240,242 and 243 can shift, to increase or to reduce radius 240,242 and 243. At some some place of the length along the second conduit portion 230, first curvature radius 240 and second curvature radius 242 can be different from each other, and at other some place, first curvature radius 240 and second curvature radius 242 can be identical. Alternatively, first curvature radius 240 and second curvature radius 242 can be different along the whole length of the first curved wall 236 and the second curved wall 238. In certain embodiments, the difference between first curvature radius 240 and second curvature radius 242 can in about scope between 0-50%, 10-40%, or 20-30%. Such as, difference can be about 15,20,25,30 or 35%, or any percentage ratio between. In certain embodiments, first curvature radius 240 can more than second curvature radius 242. In an alternative embodiment, second curvature radius 242 can more than first curvature radius 240. In other embodiments, first curvature radius 240 and second curvature radius 242 can be identical.
In certain embodiments, first curvature radius 240 can in the scope of about 30 centimetres-390 centimetres, 80-340 centimetre, 130-390 centimetre, 180-300 centimetre or 220-260 centimetre. Such as, first curvature radius 240 can be about 30,40,50,60,70,80,90 or 100 centimetres, or any distance between. In certain embodiments, first curvature radius 240 can at least above or equal to about 100 centimetres. In certain embodiments, second curvature radius 242 can in the scope of about 30 centimetres-510 centimetres, 80-460 centimetre, 130-410 centimetre, 180-360 centimetre or 230-310 centimetre. Such as, second curvature radius 242 can be about 30,40,50,60,70,80,90 or 100 centimetres, or any distance between. In certain embodiments, first curvature radius 240 can at least above or equal to about 100 centimetres. In certain embodiments, the radius 243 bending flow path 232 can in the scope of about 30 centimetres-450 centimetres, 80-400 centimetre, 130-350 centimetre, 180-300 centimetre or 220-260 centimetre. Such as, radius 243 can be about 30,40,50,60,70,80,90 or 100 centimetres, or any distance between. In certain embodiments, radius 243 can at least above or equal to about 30 centimetres. In other embodiments, radius 243 can at least above or equal to about 100 centimetres.
The curvature of wall 236 and 238 provides smoother and more aerodynamic quality flow path transition, which obviates for the demand of internal turn blade in the second conduit portion 230. Thus, axially-radial diffuser section 204 does not include any internal turn blade. Open it practice, the first curved wall 236 and the second curved wall 238 are diverging from one another respectively along bending flow path 232, with diffusion bigger during being allowed in from axial transitions to radial direction. Second conduit portion 230 of bending has the second cross-sectional area 244 (that is, being perpendicular to centrage 208), and this second cross-sectional area 244 extends between the first curved wall 236 and the second curved wall 238 along bending flow path 232. In other words, cross-sectional area 244 has the cross-sectional width 246 extended along bending flow path 232. The diffusion increasing stream is allowed in the extension of the cross-sectional width 246 in axially-radial diffuser section 204, also makes stream from axial transitions to radial direction simultaneously.
In certain embodiments, radius 240,242 and 243 can be at least about 1-100,1-50,1-25, or the 1-10 times of the cross-sectional width 246 of bending flow path 232. Such as, radius 240,242 and 243 can at least above or equal to about 1.5,2,3,4,5,6,7,8,9 or 10 times of cross-sectional width 246.
Flow and transit to radial diffuser section 206 from axially-radial diffuser section 204. Axially-radial diffuser section 204 is connected on radial diffuser section 206. Radial diffuser section 206 includes the 3rd conduit portion 248, and the 3rd conduit portion 248 has radial flow path 234 along the centrage 208 of bubbler 188. 3rd conduit portion 248 includes the first vertical wall 250 of deviation the second vertical wall 252. Additionally, the first vertical wall 250 and the second vertical wall 252 are arranged to about bending flow path 234 relative to each other. First curved wall 236 dispersed of the second conduit portion 230 and the second curved wall 238 extend respectively in the first vertical wall 250 and the second vertical wall 252. First vertical wall 250 is dispersed from the second vertical wall 252 also along radial flow path 234. As a result, the 3rd conduit portion 248 includes the 3rd cross-sectional area 254 (that is, being perpendicular to centrage 208), and it extends between the first vertical wall 250 and the second vertical wall 252 along radial flow path 234, to increase diffusion and bubbler performance. Stream is directed to the outlet 210 of bubbler 188 from radial diffuser section 206.
Fig. 3 is the perspective view of exhaust diffuser 188, it is shown that the profile of bubbler 188 and extension. As it has been described above, exhaust diffuser 188 includes axially diffusing device section 202, axially-radial diffuser section 204 and radial diffuser section 206. Axially diffuse device section 202 and include the first wall 216 and the second wall 218. Axially-radial diffuser section 204 includes the first curved wall 236 and the second curved wall 238. Both first wall 216 and the second wall 218, and at least part of first curved wall 236 and the second curved wall 238 include the semi-circular curvature of the longitudinal axis 158 transverse to gas-turbine unit 118 on the circumferencial direction that arrow 262 indicates. The annular curvature of wall 216,218,236 and 238 allows the exhaust diffuser 188 annular spread around turbine 130 exports. In certain embodiments, one or more exhaust diffusers 188 can be distributed in around the outlet of turbine 130. As shown in Figure 3, exhaust diffuser 188 includes following the 3rd wall 264 and the 4th wall 266 of the flow path generally limited by centrage 208. 3rd wall 264 and the 4th wall 266 are oppositely located relative to each other, and are positioned between the first wall 216 and second wall the 218, first curved wall 236 and the second curved wall 238 and the first vertical wall 250 and the second vertical wall 252 along the length of bubbler 188. 3rd wall 264 and the 4th wall 266 are diverging from one another to outlet 210 from entrance 192 along downstream direction 268. It addition, in both vertical dimension 270 and horizontal size 272, the cross-sectional area (that is, being perpendicular to downstream direction 268) of exhaust diffuser 188 downstream extends to the outlet 210 of bubbler 188 from entrance 192. Size 270 can be defined as the radial dimension relative to axis 158, and size 272 can be defined as the circumferential size relative to axis 158.
According to some embodiment, exhaust diffuser 188 above can operation collaborative with turbine 130. Such as, operational approach may be included in and makes the exhaust stream from turbine carry out axially-radial diffusion by the conduit bent along the flow path 232 bent when not having any steering blade, and the flow path 232 wherein bent has the radius 243 of amplification to reduce flow separation and the pressure loss. In certain embodiments, radius 243 can at least above or equal to 1-10 times of about 30 centimetres and/or width 246. In other embodiments, radius 243 can at least above or equal at least 2 times of width 246. It addition, in the method, exhaust stream axial-radial diffusion can include making exhaust stream expand between the first curved wall 236 and the second curved wall 238 that bend along bending flow path 232. As discussed above, the first curved wall 236 can be oriented to than second curved wall 238 rotation axis 220 closer to turbine 130. The method may additionally include axially-radial diffusion exhaust stream before make exhaust stream axially spread. Axially diffusing exhaust stream to include making exhaust stream expand between the first angled wall 216 and the second angled wall 218, these walls constitute angle relative to axial flow path 214. As discussed above, the first angled wall 216 can be oriented to than the second angled wall 218 rotation axis 220 closer to turbine 230.
The technique effect of the disclosed embodiments includes providing angled wall 216 and 218, thus providing stream diffusion in advance, to reduce the pressure loss crossing over pillar 190. It addition, angled wall 216 and 218 is allowed further smoothly transits to axially-radial diffuser section 204 from axially diffusing device section 202, in order at flow direction from axially reducing the pressure loss during radially changing. There is provided curved wall 236 and 238 also can make axially-the transitions smooth of radial direction for axially-radial diffuser section, eliminate the demand for steering blade simultaneously. Additionally, axially the divergent wall of diffuser section 202, axially-radial diffuser section 204 and radial diffuser section 206 allows that stream expands along flow path, and improve bubbler performance. In general, the aerodynamic design of bubbler 188 improves bubbler performance, eliminates the source (i.e. steering blade) of performance loss and mechanical problem simultaneously.
This written description uses examples to disclose the present invention, including optimal mode, and also enables those skilled in the art to put into practice the present invention, including manufacturing and utilizing any device or system, and performs any combined method. The present invention can the scope of granted patent be defined by the claims, and can include other example that those of skill in the art expect. If these other examples have the structural detail being not different from claim literal language, if or it include with claim literal language without essence difference equivalence structural detail, then these other examples are intended to belong in scope of the claims.
Claims (10)
1. a turbine system, including:
Combustion gas turbine bubbler, comprising:
Axially diffuse device section, it the first conduit portion including there is axial flow path along the centrage of described combustion gas turbine bubbler, wherein said first conduit portion has along described axial flow path with away from the first axial direction of rotation axis and the first cross-sectional area of extending towards the second axial direction of described rotation axis; With
Axially diffuse described in being connected in device section axial-radial diffuser section, wherein said axially-radial diffuser section includes the second conduit portion, described second conduit portion has the bending flow path leading to radial flow path along described centrage from described axial flow path, described second conduit portion has the second cross-sectional area extended along described bending flow path, described axially-radial diffuser do not include any steering blade in described second conduit portion.
2. turbine system according to claim 1, it is characterized in that, described combustion gas turbine bubbler include being connected in described axially-radial diffuser section on radial diffuser section, described radial diffuser section includes the 3rd conduit portion, described 3rd conduit portion has radial flow path along the centrage of described combustion gas turbine bubbler, and described 3rd conduit portion has the 3rd cross-sectional area extended along described radial flow path.
3. turbine system according to claim 1, it is characterised in that described second conduit portion includes first curved wall relative to each other about described bending flow path and the second curved wall, and the radius of curvature of described first curved wall is more than or equal to 100 centimetres.
4. turbine system according to claim 1, it is characterized in that, described second conduit portion includes the first curved wall of deviation the second curved wall, described first curved wall bends along described bending flow path with first curvature radius, and described second curved wall bends along described bending flow path with second curvature radius.
5. turbine system according to claim 4, it is characterised in that described first curved wall is close relative to the rotation axis of combustion gas turbine, and described second curved wall relative to described combustion gas turbine rotation axis away from.
6. turbine system according to claim 4, it is characterised in that described first curvature radius and described second curvature radius are mutually the same.
7. turbine system according to claim 4, it is characterised in that described first curvature radius and described second curvature radius are different from each other.
8. turbine system according to claim 4, it is characterised in that described first curved wall and described second curved wall are diverging from one another along described bending flow path.
9. turbine system according to claim 1, it is characterized in that, described first conduit portion includes the first wall of deviation the second wall, described first wall is close relative to the rotation axis of combustion gas turbine, and described second wall relative to described combustion gas turbine rotation axis away from, and described first wall and described second wall diverging from one another along described axial flow path.
10. turbine system according to claim 9, it is characterized in that, described first wall extends with the first angle along described axial flow path relative to described rotation axis, described second wall extends with the second angle along described axial flow path relative to described rotation axis, and described first angle and described second angle are not 0 degree.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/852129 | 2010-08-06 | ||
| US12/852,129 US20120034064A1 (en) | 2010-08-06 | 2010-08-06 | Contoured axial-radial exhaust diffuser |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102374030A CN102374030A (en) | 2012-03-14 |
| CN102374030B true CN102374030B (en) | 2016-06-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110230203.6A Expired - Fee Related CN102374030B (en) | 2010-08-06 | 2011-08-05 | Curvilinear axially-radially exhaust diffuser |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20120034064A1 (en) |
| JP (1) | JP6059424B2 (en) |
| CN (1) | CN102374030B (en) |
| CH (1) | CH703553B1 (en) |
| DE (1) | DE102011052236A1 (en) |
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| KR102587343B1 (en) * | 2018-10-15 | 2023-10-10 | 한화에어로스페이스 주식회사 | Low loss curved pipe exhaust duct |
| CN109372637B (en) * | 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 (en) * | 2018-12-16 | 2022-03-04 | 中国航发沈阳发动机研究所 | Gas turbine exhaust apparatus |
| CN109578141B (en) * | 2019-01-23 | 2023-10-20 | 中国船舶重工集团公司第七0三研究所 | Exhaust volute of reversing gas turbine power turbine |
| KR20210090501A (en) * | 2020-01-10 | 2021-07-20 | 한화에어로스페이스 주식회사 | Exhaust duct and exhaust duct assembly and aircraft using the exhaust duct |
| JP7458947B2 (en) * | 2020-09-15 | 2024-04-01 | 三菱重工コンプレッサ株式会社 | Steam turbine |
| DE112022000513T5 (en) * | 2021-03-24 | 2024-01-25 | Mitsubishi Heavy Industries, Ltd. | TURBINE AND GAS TURBINE |
| US11391296B1 (en) * | 2021-07-07 | 2022-07-19 | Pratt & Whitney Canada Corp. | Diffuser pipe with curved cross-sectional shapes |
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| CN1116271A (en) * | 1994-06-29 | 1996-02-07 | Abb管理有限公司 | Diffuser for turbine machine |
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| US5603605A (en) * | 1996-04-01 | 1997-02-18 | Fonda-Bonardi; G. | Diffuser |
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| JPS5965907U (en) * | 1982-10-25 | 1984-05-02 | 富士電機株式会社 | Turbine exhaust diffuser |
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| US6544357B1 (en) * | 1994-08-01 | 2003-04-08 | Franz Hehmann | Selected processing for non-equilibrium light alloys and products |
| GB9415685D0 (en) * | 1994-08-03 | 1994-09-28 | Rolls Royce Plc | A gas turbine engine and a diffuser therefor |
| JP4114253B2 (en) * | 1998-11-30 | 2008-07-09 | 株式会社Ｉｈｉ | Gas turbine exhaust casing |
| US6488470B1 (en) * | 1999-08-03 | 2002-12-03 | Jerzy A. Owczarek | Annular flow diffusers for gas turbines |
| DE10037684A1 (en) * | 2000-07-31 | 2002-02-14 | Alstom Power Nv | Low pressure steam turbine with multi-channel diffuser |
| US6802690B2 (en) * | 2001-05-30 | 2004-10-12 | M & I Heat Transfer Products, Ltd. | Outlet silencer structures for turbine |
| US20050042087A1 (en) * | 2003-05-28 | 2005-02-24 | Hamer Andrew J. | Method and apparatus for reducing total pressure loss in a turbine engine |
| GB2442422B8 (en) * | 2005-08-04 | 2015-12-16 | Rolls Royce Power Eng | Gas turbine exhaust diffuser |
| US8439633B2 (en) * | 2010-01-04 | 2013-05-14 | General Electric Company | Hollow steam guide diffuser having increased pressure recovery |
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2010
- 2010-08-06 US US12/852,129 patent/US20120034064A1/en not_active Abandoned
-
2011
- 2011-07-28 DE DE102011052236A patent/DE102011052236A1/en not_active Withdrawn
- 2011-08-02 CH CH01286/11A patent/CH703553B1/en not_active IP Right Cessation
- 2011-08-02 JP JP2011168855A patent/JP6059424B2/en not_active Expired - Fee Related
- 2011-08-05 CN CN201110230203.6A patent/CN102374030B/en not_active Expired - Fee Related
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5603604A (en) * | 1990-11-21 | 1997-02-18 | Norlock Technologies, Inc. | Method and apparatus for enhancing gas turbo machinery flow |
| CN1116271A (en) * | 1994-06-29 | 1996-02-07 | Abb管理有限公司 | Diffuser for turbine machine |
| US5603605A (en) * | 1996-04-01 | 1997-02-18 | Fonda-Bonardi; G. | Diffuser |
Also Published As
| Publication number | Publication date |
|---|---|
| CH703553A2 (en) | 2012-02-15 |
| DE102011052236A1 (en) | 2012-02-09 |
| CH703553B1 (en) | 2016-02-29 |
| US20120034064A1 (en) | 2012-02-09 |
| CN102374030A (en) | 2012-03-14 |
| JP6059424B2 (en) | 2017-01-11 |
| JP2012036891A (en) | 2012-02-23 |
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