EP2318664B1 - Dispositif de turbine à gaz avec conduit de transition non cylindrique - Google Patents
Dispositif de turbine à gaz avec conduit de transition non cylindrique Download PDFInfo
- Publication number
- EP2318664B1 EP2318664B1 EP09807919.7A EP09807919A EP2318664B1 EP 2318664 B1 EP2318664 B1 EP 2318664B1 EP 09807919 A EP09807919 A EP 09807919A EP 2318664 B1 EP2318664 B1 EP 2318664B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- inner casing
- hub
- turbine
- inner housing
- bosses
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Not-in-force
Links
Images
Classifications
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2210/00—Working fluids
- F05D2210/40—Flow geometry or direction
- F05D2210/43—Radial inlet and axial outlet
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/80—Repairing, retrofitting or upgrading methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/313—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being perpendicular to each other
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/33—Arrangement of components symmetrical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
Definitions
- the present invention relates to a gas turbine arrangement comprising at least one burner and a combustion chamber for combusting fuel, a mixing housing and an adjoining inner housing and a turbine arranged substantially perpendicularly with respect to the at least one burner, wherein the combustion exhaust gas resulting from the combustion of the fuel flows through the mixing housing in the inner housing, wherein the inner housing is configured such that the combustion exhaust gas is deflected in the inner housing in the direction of the turbine. Furthermore, the invention relates to a gas turbine.
- a gas turbine plant 1 essentially comprises one or more combustion chambers 3 with burners 13 (cf. FIG. 2 ), in which a fuel is burned, a turbine 5, which are supplied to the hot and pressurized combustion exhaust gases from the combustion chambers 3 and in which the exhaust work under cooling and relaxation work and so put the turbine 5 in rotation, and a compressor 7, which is coupled to the turbine 5 via a shaft 12 which is surrounded by a hub 17, and via which the air necessary for the combustion is sucked in and compressed to a higher pressure.
- FIG. 1 shows such a gas turbine plant in a schematic view, wherein FIG1 shows a horizontal section through the plant.
- the combustion exhaust gases 2 flow in a direction which is substantially perpendicular to a rotation axis A of the turbine 5.
- a mixing housing 8 is arranged, which is adjoined on the turbine side by an inner housing 9 arranged in the interior of the gas turbine housing 2.
- the inner housing 9 has the task to protect the surrounding components from heat and to redirect the exiting the mixing housing 8 hot exhaust gases in the direction of the turbine 5.
- the gas in the inner housing 9 is deflected substantially by 90 ° degrees and then fed via a common annular space of the turbine. Due to the shape of the housing, there is no clear guidance of the two gas streams from the two silo separation chambers 3 to the turbine 5, that is to say the streams impinge on the hub 17 and are then distributed to the circulating space for turbine entry. This results in an inhomogeneous flow of the turbine 5. This is to be expected with performance losses.
- the GB 2 361 302 A far an arcuate inner housing formed with an inner housing hub having ribs or furrows.
- the first object is achieved by a gas turbine arrangement according to claim 1.
- the object related to the gas turbine is solved by specifying a gas turbine according to claim 6.
- the dependent claims contain advantageous embodiments of the invention.
- a gas turbine arrangement comprises at least one burner and a combustion chamber for combusting fuel, a mixing housing and an adjoining inner housing with inner housing hub and a turbine arranged substantially perpendicular with respect to the at least one burner.
- the combustion exhaust gas produced by the combustion of the fuel flows through the mixing housing into the inner housing, wherein the inner housing is designed such that the combustion exhaust gas is deflected in the inner housing by means of the inner housing hub in the direction of the turbine. This is essentially a 90 degree deflection. Since, due to the shape of the housing, no clear guidance of the gas flow to the turbine, there is an inhomogeneous flow.
- the inner housing hub has at least two bosses, wherein the at least two bosses are arranged offset to an inner housing inlet, so that the incoming combustion exhaust gas stream in its entirety is deflected around the inner housing hub.
- the at least two projections have approximately the shape of a lemon with the inner housing hub. This results in a homogenization of the hot gas flows of the exhaust gas or the Exhaust gas flow, whereby an improved turbine flow is achieved.
- the humps can be variably designed with respect to their length in the A-axis direction.
- the humps are preferably symmetrical with respect to a B-axis. Impacted exhaust gas is now better diverted by the aerodynamic shape of the inner housing hub.
- the at least two projections are fastened by being attached to the inner housing hub. This can also be partial welding to the hub. Already manufactured hubs can be retrofitted with it. Furthermore, it is also possible to manufacture the at least two projections firmly on the inner housing hub. Preferably, the at least two projections are designed as a hollow body or as a solid body.
- the at least two bosses are arranged opposite one another on the inner housing hub.
- the exhaust gases are deflected symmetrically.
- a gas turbine which comprises at least two essentially oppositely located burners and combustion chambers for combustion of fuel.
- This can be especially known Silobrennschn.
- the inner housing hub has at least two opposing humps. Due to this improved aerodynamic shape of the inner housing hub, the Verbrennüngsabgas is thus better redirected.
- the exhaust gas flow coming from the mixing housing is essentially deflected or divided and deflected in its entirety in one direction. As a result, both a better deflection of the exhaust gas and an improved flow of the turbine is achieved.
- the at least two humps are offset to an inner housing entry arranged so that the incoming combustion exhaust gas stream in its entirety is deflected around the inner housing hub.
- the at least two projections have approximately the shape of a lemon with the inner housing hub. This results in a homogenization of the hot gas flows of the exhaust gas or the exhaust gas flow, whereby an improved turbine flow is achieved.
- the individual turbine blades are flown according to their design. This improves the performance of the turbine.
- gas turbine plant 1 An example of gas turbine plant 1 is in the FIG. 1 shown in a highly schematic representation.
- the gas turbine plant 1 comprises two silo separation chambers 3, a turbine 5, a compressor 7, two mixing housings 8 and an inner housing 9.
- the silo combustion chambers 3 are used for combustion a fuel, wherein the hot and high-pressure exhaust gases 2 are supplied via the mixing housing 8 and the inner housing 9 of the turbine 5 to drive them.
- the turbine 5 comprises stationary guide vanes 10 and rotor blades 11 fixedly connected to a shaft 12 rotatably mounted about an axis A.
- the hot exhaust gas 2 expanding in the turbine 5 transmits impulse to the shaft 12 via the rotor blades 11, causing them to rotate becomes.
- the shaft 12 can be roughly divided into three sections, namely a section carrying the blades 11 of the turbine 5, a rotor blade of the compressor 7 (not shown) and a shaft section 16 arranged between these two sections, in which no blades are arranged.
- the shaft 12 and the attached blades 11 form the so-called. Turbine rotor.
- the shaft 12 extends through the entire gas turbine plant (not fully shown) and drives the compressor 7 and a generator, not shown.
- the compressor 7 serves to compress air, which is then fed to the silo combustion chambers 3 for combustion.
- FIG. 2 shows a vertical section through the silo combustion chamber 3 with burners 13 a subsequent mixing housing 8 and an inner housing 9.
- the combustion chamber 3 as the burner 13 are vertical and are located at the top of the figure shown.
- the conical and curved mixing housing connects, that the combustion exhaust gases leads to the inner housing 9.
- the shaft 12 is of a wave protection jacket 15 (see. FIG. 3 ), which itself is surrounded by an inner housing hub 17 of the inner housing 9.
- FIG. 3 shows the inner housing with inner housing hub 17 (vertical section through the inner housing), in which the inner housing hub 17 of the inner housing 9 and a part of the wave protection jacket 15 can be seen.
- a guide vane 10 of the turbine 5 can be seen, which is opposite to the turbine-side opening 19 of the inner housing 9.
- the inner housing hub 17 and the shaft protection jacket 15 have substantially the shape of a hollow cylinder.
- the inner housing 9 serves to deflect the hot exhaust flowing from the mixing housings 8 into the inner housing 9 on the one hand and to distribute it as evenly as possible around the entire circumference of the turbine runner on the other hand. Here, the deflection is done by about 90 ° degrees.
- the gases are then fed to the turbine via a common annulus. Due to the shape of the mixing housing 8, there is no clear guidance of the two exhaust gas flows to the turbine, that is to say the flows impinge on the hub 17 at the level of a parting line (not shown) and then distribute themselves on the surrounding space Turbine inlet. This results in an inhomogeneous flow to the turbine, which is expected to result in performance losses.
- FIG. 4 schematically shows an inner housing 9 and the inner housing hub 170 according to the invention and the turbine inlet 20 of a gas turbine with Silobrennschn 3.
- the inner housing hub 170 is provided with two bosses 23a, 23b in these embodiments.
- the inner housing hub 170 thus essentially has the shape of a lemon.
- the humps 23a, 23b are symmetrical to an axis of symmetry B.
- Incoming exhaust gas streams 22a, 22b are now redirected by these humps 23a, 23b aerodynamically improved, so no longer bounce as in the inner housing hub 17 according to the prior art substantially perpendicular to the hub , This results in a homogenization of the hot gas flow in the inner housing, whereby the turbine is better flowed.
- the turbine blades 10,11 can be flown according to their design. This results in improved performance values of the turbine 5.
- flow accumulation points in the inner housing 9 and on the hub 170 are avoided.
- the wear of the individual components is avoided by erosion and oxidation.
- the humps are arranged offset to the inner housing inlet 25.
- the incoming exhaust gas stream 22a (and 22b) is deflected substantially all around the inner housing hub 170.
- it is gas turbines with two Silobrennsch 3. The number of
- Humps 23a, 23b and the size of the humps 23a, 23b can therefore vary depending on the gas turbine type and design of the individual gas turbine.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (6)
- Agencement de turbine à gaz, comprenant au moins un brûleur (13) et une chambre de combustion (3) pour brûler du combustible, une enveloppe (8a, b) de mélange, ainsi qu'une enveloppe (9), s'y raccordant et ayant un moyeu (170) d'enveloppe intérieure, et une turbine (5) disposée sensiblement perpendiculairement au au moins un brûleur (3), les gaz (22a, 22b) perdus de combustion allant dans l'enveloppe (9) intérieure en passant par l'enveloppe (8a, b) de mélange, l'enveloppe (9) intérieure étant conformée de manière à dévier le gaz (22a, 22b) perdus de combustion dans l'enveloppe (9) intérieure au moyen du moyeu (170) de l'enveloppe intérieure en direction de la turbine (5), le moyeu (170) de l'enveloppe intérieure ayant au moins deux renflements (23a), (23b), les au moins deux renflements (23a), (23b) étant décalés par rapport à une entrée (25) de l'enveloppe intérieure, de manière à dévier dans sa totalité autour du moyeu (170) de l'enveloppe intérieure le courant (22a, 22b) des gaz perdus de combustion arrivant, caractérisé en ce que les au moins deux renflements (23a), (23b) ont, avec le moyeu (170) de l'enveloppe intérieure, à peu près la forme d'un citron.
- Agencement de turbine à gaz suivant la revendication 1, caractérisé en ce qu'au moins deux renflements (23a), (23b) sont fixés par enfichage au moyeu (170) de l'enveloppe intérieure.
- Agencement de turbine à gaz suivant la revendication 1, caractérisé en ce que les au moins deux renflements (23a), (23b) sont fabriqués de manière fixe sur le moyeu (170) de l'enveloppe intérieure.
- Agencement de turbine à gaz suivant l'une des revendications précédentes, caractérisé en ce que les au moins deux renflements (23a), (23b) sont réalisés sous la forme d'une pièce creuse ou d'une pièce pleine.
- Agencement de turbine à gaz suivant l'une des revendications précédentes, caractérisé en ce que les au moins deux renflements (23a), (23b) sont disposés en se faisant face sur le moyeu (170) de l'enveloppe intérieure.
- Turbine (5) à gaz, comprenant au moins deux brûleurs (13) et chambres de combustion (3) se faisant face sensiblement pour brûler du combustible, ainsi qu'une enveloppe (8a), (8b) de mélange s'y raccordant, respectivement et une enveloppe (9) intérieure s'y raccordant, ainsi qu'un moyeu (170) d'enveloppe intérieure disposé autour d'un arbre (12), dans laquelle le moyeu (170) de l'enveloppe intérieure a au moins deux renflements (23a), (23b) qui se font face, les renflements (23a), (23b) étant disposés de manière décalée par rapport à une entrée (25) de l'enveloppe intérieure de manière à ce que le courant (22a, 22b) des gaz perdus de combustion arrivant soit dévié dans sa totalité autour du moyeu (170) de l'enveloppe intérieure,
caractérisé en ce que les au moins deux renflements (23a, 23b) ont, avec le moyeu (170) de l'enveloppe intérieure, à peu près la forme d'un citron.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09807919.7A EP2318664B1 (fr) | 2008-08-21 | 2009-07-16 | Dispositif de turbine à gaz avec conduit de transition non cylindrique |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP08014872A EP2157284A1 (fr) | 2008-08-21 | 2008-08-21 | Dispositif de turbine à gaz avec conduit de transition non cylindrique et procédé pour diriger l'écoulement sur la turbine |
EP09807919.7A EP2318664B1 (fr) | 2008-08-21 | 2009-07-16 | Dispositif de turbine à gaz avec conduit de transition non cylindrique |
PCT/EP2009/059126 WO2010020487A1 (fr) | 2008-08-21 | 2009-07-16 | Agencement de turbine à gaz comportant moyeu de boîtier interne non cylindrique et procédé pour le flux abordant une turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2318664A1 EP2318664A1 (fr) | 2011-05-11 |
EP2318664B1 true EP2318664B1 (fr) | 2016-05-04 |
Family
ID=40849151
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08014872A Withdrawn EP2157284A1 (fr) | 2008-08-21 | 2008-08-21 | Dispositif de turbine à gaz avec conduit de transition non cylindrique et procédé pour diriger l'écoulement sur la turbine |
EP09807919.7A Not-in-force EP2318664B1 (fr) | 2008-08-21 | 2009-07-16 | Dispositif de turbine à gaz avec conduit de transition non cylindrique |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08014872A Withdrawn EP2157284A1 (fr) | 2008-08-21 | 2008-08-21 | Dispositif de turbine à gaz avec conduit de transition non cylindrique et procédé pour diriger l'écoulement sur la turbine |
Country Status (2)
Country | Link |
---|---|
EP (2) | EP2157284A1 (fr) |
WO (1) | WO2010020487A1 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102015207760A1 (de) * | 2015-04-28 | 2016-11-03 | Siemens Aktiengesellschaft | Heißgasführendes Gehäuse |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3117515C2 (de) * | 1980-05-07 | 1983-11-10 | Brown, Boveri & Cie Ag, 6800 Mannheim | Überströmgehäuse |
GB2293232B (en) * | 1994-09-15 | 1998-05-20 | Rolls Royce Plc | A combustion chamber assembly |
GB2361302A (en) * | 2000-04-13 | 2001-10-17 | Rolls Royce Plc | Discharge nozzle for a gas turbine engine combustion chamber |
-
2008
- 2008-08-21 EP EP08014872A patent/EP2157284A1/fr not_active Withdrawn
-
2009
- 2009-07-16 EP EP09807919.7A patent/EP2318664B1/fr not_active Not-in-force
- 2009-07-16 WO PCT/EP2009/059126 patent/WO2010020487A1/fr active Application Filing
Also Published As
Publication number | Publication date |
---|---|
EP2157284A1 (fr) | 2010-02-24 |
EP2318664A1 (fr) | 2011-05-11 |
WO2010020487A1 (fr) | 2010-02-25 |
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