EP2318664A1 - Agencement de turbine à gaz comportant moyeu de boîtier interne non cylindrique et procédé pour le flux abordant une turbine - Google Patents

Agencement de turbine à gaz comportant moyeu de boîtier interne non cylindrique et procédé pour le flux abordant une turbine

Info

Publication number
EP2318664A1
EP2318664A1 EP09807919A EP09807919A EP2318664A1 EP 2318664 A1 EP2318664 A1 EP 2318664A1 EP 09807919 A EP09807919 A EP 09807919A EP 09807919 A EP09807919 A EP 09807919A EP 2318664 A1 EP2318664 A1 EP 2318664A1
Authority
EP
European Patent Office
Prior art keywords
inner housing
turbine
gas turbine
hub
combustion
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.)
Granted
Application number
EP09807919A
Other languages
German (de)
English (en)
Other versions
EP2318664B1 (fr
Inventor
Andre Botzen
Karl Klein
Marco Link
Oliver Lüsebrink
Nicolas Savilius
Oliver Schneider
Marc Tertilt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP09807919.7A priority Critical patent/EP2318664B1/fr
Publication of EP2318664A1 publication Critical patent/EP2318664A1/fr
Application granted granted Critical
Publication of EP2318664B1 publication Critical patent/EP2318664B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 and a method for Turbinenanströmung.
  • a gas turbine installation 1 essentially comprises one or more combustion chambers 3 with burners 13 (see FIG. 2) in which a fuel is burnt, a turbine 5 which extracts the hot and pressurized combustion exhaust gases from the combustion chambers 3 be fed 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 on the sucked in the necessary air for combustion and compressed to a higher pressure.
  • FIG. 1 shows such a gas turbine plant in a schematic view, wherein FIGl shows a horizontal section through the system.
  • the combustion 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.
  • Gas turbine plant 1 then flow the combustion exhaust gases substantially parallel to the axis of rotation A of the turbine shaft 12th
  • Inner housing 9 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.
  • Another object of the present invention is to provide an improved gas turbine assembly which ensures improved turbine flow. Another task is the specification of such a gas turbine. Another object is to specify a method based on improved turbine flow.
  • 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 9.
  • the object related to the method is solved by claim 10.
  • 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 resulting from the combustion of the fuel flows through the mixing housing into the inner housing, wherein the inner housing is configured such that the combustion exhaust gas in the inner housing by means of
  • Inner housing hub is deflected towards 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. Here, the invention intervenes, and solves this long-standing problem by the réellegeophusenabe is non-cylindrical, whereby the turbine is better flowed. As a result, the combustion exhaust gases are better deflected and substantially no longer bounce perpendicular to the inner housing hub. This makes it possible to feed the individual turbine blades according to their design.
  • the inner housing hub has at least one projection. Depending on the design of the combustion chamber and mixing housing, this projection is variable in terms of its length in the A-axis direction.
  • the hump is preferably symmetrical with respect to a B-axis.
  • the at least one projection is attached 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 that at least one hump firmly on the
  • the at least one projection is designed as a hollow body or as a solid body.
  • At least two humps are present. This is particularly advantageous when the combustion chambers are so-called silo combustion chambers.
  • the at least two bosses are arranged opposite one another on the inner housing hub.
  • the exhaust gases are deflected symmetrically.
  • the at least two projections with the inner housing hub approximately the shape of a lemon. 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.
  • 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 combustion exhaust gas is thus better diverted. Indeed, once the humps are located on the inner shell hub, the exhaust stream coming from the mixing shell is substantially diverted or split and deflected in its entirety. As a result, both a better deflection of the exhaust gas and an improved flow of the turbine is achieved.
  • a method for turbine flow is disclosed, which comprises a burner and a combustion chamber, in which fuel is combusted to combustion exhaust gases, and a mixing housing and an adjoining inner housing for guiding the
  • Combustion exhaust gases to a turbine which is arranged substantially perpendicular to the flow direction of the combustion exhaust gases in the combustion chamber, wherein in the inner housing by means of a mecanicgephaseusenabe the combustion exhaust gases are deflected toward the turbine, wherein by applying at least one projection on the mecanicalenabe improves the flow diversion of the combustion exhaust gas flow in the inner housing so that a better turbine flow is achieved.
  • the individual turbine blades are flown according to their design. This improves the performance of the turbine.
  • Silo combustion chamber, the mixing housing and the inner housing according to the prior art, 3 shows a detail of an inner housing and associated inner housing hub according to the prior art
  • FIG 5 shows schematically a further embodiment of the inner housing hub according to the invention with two bosses.
  • FIG. 1 An example of gas turbine plant 1 is shown in FIG. 1 in a highly schematic representation.
  • the gas turbine plant 1 comprises two silo combustion chambers 3, a turbine 5, a compressor 7, two mixing housings 8 and an inner housing 9.
  • the silo combustion chambers 3 serve to burn a fuel, the hot exhaust gases 2 under high pressure being supplied via the mixing housings 8 and the inner housing 9 of the turbine 5 are supplied to drive these.
  • 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 upper end 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 surrounded by 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 and FIG. 5 schematically show an inner housing 9 and the inner housing hub 170 and the turbine inlet 20 of a gas turbine with silo combustion chambers 3.
  • the exhaust gas flow from both mixing housings 8a, 8b has to have a defined guidance from Admission to the inner housing 9 to the turbine inlet 20 experienced.
  • 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 aerodynamically improved by these humps 23a, 23b deflected, 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. As a result, the wear of the individual components is avoided by erosion and oxidation.
  • the bosses 23a, 23b can be arranged directly opposite the inner housing inlet 25, which represents the transition from the mixed housing 8a, 8b and inner housing 9.
  • the incoming exhaust gas stream 22a, 22b is divided into two parts and the resulting streams are then distributed around the inner housing hub 170.
  • the projections are offset from the inner housing inlet 25.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un agencement de turbine à gaz comprenant au moins un brûleur (13) et une chambre de combustion (3) pour la combustion de combustible, un boîtier de mélange (8a, b) et un boîtier interne (9) s'y raccordant, doté d'un moyeu de boîtier interne (170), et une turbine (5) disposée de manière sensiblement perpendiculaire au(x) brûleur(s) (13). Le gaz brûlé de combustion se formant du fait de la combustion du combustible traverse le boîtier de mélange (8a, b) et entre dans le boîtier interne (9). Le boîtier interne (9) est conçu de telle sorte que le gaz brûlé de combustion dans le boîtier interne (9) est dévié au moyen du moyeu de boîtier interne (170) en direction de la turbine (5), le moyeu de boîtier interne (170) étant conçu de manière non cylindrique. L'invention concerne également une turbine à gaz et un procédé pour un flux optimisé abordant une turbine.
EP09807919.7A 2008-08-21 2009-07-16 Dispositif de turbine à gaz avec conduit de transition non cylindrique Not-in-force EP2318664B1 (fr)

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
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
EP09807919.7A EP2318664B1 (fr) 2008-08-21 2009-07-16 Dispositif de turbine à gaz avec conduit de transition non cylindrique

Publications (2)

Publication Number Publication Date
EP2318664A1 true EP2318664A1 (fr) 2011-05-11
EP2318664B1 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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015207760A1 (de) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Heißgasführendes Gehäuse

Family Cites Families (3)

* Cited by examiner, † Cited by third party
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010020487A1 *

Also Published As

Publication number Publication date
EP2318664B1 (fr) 2016-05-04
EP2157284A1 (fr) 2010-02-24
WO2010020487A1 (fr) 2010-02-25

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