EP2157286A1 - Turbine à gaz avec conduit de mélange à angle et procédé pour diriger l'écoulement sur la turbine - Google Patents

Turbine à gaz avec conduit de mélange à angle et procédé pour diriger l'écoulement sur la turbine Download PDF

Info

Publication number
EP2157286A1
EP2157286A1 EP08014874A EP08014874A EP2157286A1 EP 2157286 A1 EP2157286 A1 EP 2157286A1 EP 08014874 A EP08014874 A EP 08014874A EP 08014874 A EP08014874 A EP 08014874A EP 2157286 A1 EP2157286 A1 EP 2157286A1
Authority
EP
European Patent Office
Prior art keywords
inner housing
turbine
housing
mixing
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.)
Withdrawn
Application number
EP08014874A
Other languages
German (de)
English (en)
Inventor
Andre Botzen
Karl Dr. Klein
Marco Link
Oliver Dr. Lüsebrink
Nicolas Savilius
Oliver Dr. 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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP08014874A priority Critical patent/EP2157286A1/fr
Publication of EP2157286A1 publication Critical patent/EP2157286A1/fr
Withdrawn legal-status Critical Current

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
    • 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
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation 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
    • F05D2250/70—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 in relation 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 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 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 over the surrounding space to the turbine inlet. This results in an inhomogeneous flow of the turbine 5. This is to be expected with performance losses.
  • 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 5.
  • the object related to the method is solved by 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 and a turbine, which is arranged vertically 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 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. This results in poor performance values.
  • the invention intervenes, and solves this long-standing problem by the mixing housing is angled relative to the inner housing, so that a better deflection of the combustion exhaust gas is effected in the direction of the turbine.
  • the mixing housing namely the exhaust gas is better redirected in the inner housing.
  • the gas turbine arrangement comprises a shaft on which the turbine is arranged.
  • the inner housing has an inner housing hub, which is arranged substantially parallel to the shaft.
  • This inner housing hub is preferably at least approximately cylindrical.
  • the angle between the inner housing and the mixing housing is designed such that Strömungsstaulie in the inner housing and on the Inner housing hub are avoided. This avoids the wear of these components due to oxidation and erosion.
  • a gas turbine which comprises at least two burners and combustion chambers that are substantially opposite each other.
  • This can be especially known Silobrennschn.
  • the mixing housing a and b and an inner housing with a arranged around a shaft closed inner housing hub.
  • an annular space is formed with a circumference.
  • the mixing housing a and b are now angled in the circumferential direction. As a result, both a better deflection and an improved flow of the turbine is achieved.
  • a method for turbine flow 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 substantially perpendicular to the flow direction of the Combustion gases is arranged in the combustion chamber, wherein the combustion gases are deflected toward the turbine in the inner housing, wherein by means of angling the mixing housing relative to the inner housing, the flow diversion is improved in the inner housing, so that an improved turbine flow is achieved.
  • the flow diversion of the exhaust gases in the inner housing is improved, which leads to a homogenization of the hot gas flow in the inner housing.
  • the flow to the turbine is made uniform, thereby improving the performance of the machine. Also Strömungsstauains be avoided in the inner housing and the hub, resulting in less wear.
  • 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 combustion chambers 3, a turbine 5, a compressor 7, two mixing housings 8 and an inner housing 9.
  • the silo combustion chambers 3 serve for burning 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 top of the figure shown.
  • the conical and curved mixing housing connects, which leads the combustion exhaust gases 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 5 via a common annular space. 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, the currents meet at the level of a parting line (not shown) on the hub 17 and then distributed to the circumferential space to the turbine inlet 20. This results in an inhomogeneous flow to the turbine 5, which is expected to performance losses is.
  • FIG. 4 schematically shows an inner housing 9 and the inner housing hub 17 and the turbine inlet 20.
  • the inner housing 9 and the hub 17 thereby form an annular space with a circumference in which the flow flows.
  • the mixing housing 80a and 80b according to the invention is angled relative to the inner housing 9 shown here in the circumferential direction. As a result, the combustion exhaust gas stream 22 is better diverted.
  • the angling of the mixing housings 80a, b improves the flow diversion in the inner housing 9, which leads to the avoidance of flow accumulation points in the inner housing 9 and on the hub 17.
  • the wear of the components is reduced by oxidation and erosion.
  • the combustion exhaust gas flow 22 is improved in the inner housing 9, which leads to a homogenization of the flow in the inner housing 9. This improves the flow of the turbine 5 and there is an improvement in the performance values.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08014874A 2008-08-21 2008-08-21 Turbine à gaz avec conduit de mélange à angle et procédé pour diriger l'écoulement sur la turbine Withdrawn EP2157286A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08014874A EP2157286A1 (fr) 2008-08-21 2008-08-21 Turbine à gaz avec conduit de mélange à angle et procédé pour diriger l'écoulement sur la turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08014874A EP2157286A1 (fr) 2008-08-21 2008-08-21 Turbine à gaz avec conduit de mélange à angle et procédé pour diriger l'écoulement sur la turbine

Publications (1)

Publication Number Publication Date
EP2157286A1 true EP2157286A1 (fr) 2010-02-24

Family

ID=40846089

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08014874A Withdrawn EP2157286A1 (fr) 2008-08-21 2008-08-21 Turbine à gaz avec conduit de mélange à angle et procédé pour diriger l'écoulement sur la turbine

Country Status (1)

Country Link
EP (1) EP2157286A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2526281A (en) * 1947-04-10 1950-10-17 Wright Aeronautical Corp Turbine and turbine nozzle construction
US3650106A (en) * 1968-10-18 1972-03-21 Bennes Marrel Sa Combustion chamber for gas turbine
EP0493004A1 (fr) * 1990-12-20 1992-07-01 Honda Giken Kogyo Kabushiki Kaisha Générateur de gaz pour une turbine à gaz
EP1391583A1 (fr) * 2002-08-23 2004-02-25 MAN Turbomaschinen AG Conduit de transition refroidi par air
DE10348447A1 (de) * 2003-10-17 2005-07-07 Siemens Ag Montage- und Wartungshilfsmittel für eine Gasturbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2526281A (en) * 1947-04-10 1950-10-17 Wright Aeronautical Corp Turbine and turbine nozzle construction
US3650106A (en) * 1968-10-18 1972-03-21 Bennes Marrel Sa Combustion chamber for gas turbine
EP0493004A1 (fr) * 1990-12-20 1992-07-01 Honda Giken Kogyo Kabushiki Kaisha Générateur de gaz pour une turbine à gaz
EP1391583A1 (fr) * 2002-08-23 2004-02-25 MAN Turbomaschinen AG Conduit de transition refroidi par air
DE10348447A1 (de) * 2003-10-17 2005-07-07 Siemens Ag Montage- und Wartungshilfsmittel für eine Gasturbine

Similar Documents

Publication Publication Date Title
DE4242494C1 (en) Adjustable flow-guide for engine exhaust turbocharger - has axially-adjustable annular insert in sectors forming different kinds of guide grilles supplied simultaneously by spiral passages
EP2179143B1 (fr) Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz
EP0799973B1 (fr) Contour de paroi pour une turbomachine axiale
EP2532898A1 (fr) Turbocompresseur axial
EP2379846B1 (fr) Structure de support d'aubes directrices pour turbomachine
EP1706597B1 (fr) Turbine a gaz avec rotor axialement deplacable
DE102011054586A1 (de) Dichtungsanordnung für eine Turbomaschine
DE102007029004A1 (de) Abgasturbolader für eine Brennkraftmaschine
EP2642098A1 (fr) Centrale de turbine à gaz avec gaz d'arrivée hétérogène
DE102007028742A1 (de) Luftversorger, insbesondere für ein Luftversorgungssystem von Brennstoffzellen
EP0928364A1 (fr) Compensation de la perte de pression d'une conduite d'air de refroidissement dans une installation de turbine a gaz
EP0532907B1 (fr) Turbine axiale
EP2183487A1 (fr) Turbomachine et procédé de production d'une turbomachine de ce type
EP3245451A1 (fr) Chambre de combustion pour turbine à gaz, délimitée par une paroi
EP1744016A1 (fr) Elément de carénage pour gaz chauds, chemise de protection de l'arbre et turbine à gaz
DE102010044819B4 (de) Axialturbine und ein Verfahren zum Abführen eines Stroms von einer Axialturbine
DE102015012259A1 (de) Turbinenrad für eine Turbine eines Abgasturboladers
EP2558781B1 (fr) Générateur de turbulence pour un brûleur
EP2318664B1 (fr) Dispositif de turbine à gaz avec conduit de transition non cylindrique
EP2987967A1 (fr) Carter de compresseur pour une turbine à gaz
DE102012002465A1 (de) Gasturbinenbrennkammer mit unsymmetrischen Kraftstoffdüsen
EP2157286A1 (fr) Turbine à gaz avec conduit de mélange à angle et procédé pour diriger l'écoulement sur la turbine
DE102011052674A1 (de) Brennstoffdüse und Verfahren zur Drallsteuerung
EP2157285A1 (fr) Dispositif de turbine à gaz et procédé pour diriger l'ecoulement sur la turbine
WO2010023034A1 (fr) Turbine à gaz comprenant un carter poreux et procédé de fabrication correspondant

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

AKY No designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20100825

REG Reference to a national code

Ref country code: DE

Ref legal event code: R108

Effective date: 20110315

Ref country code: DE

Ref legal event code: 8566