EP2224101A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

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Publication number
EP2224101A1
EP2224101A1 EP09002892A EP09002892A EP2224101A1 EP 2224101 A1 EP2224101 A1 EP 2224101A1 EP 09002892 A EP09002892 A EP 09002892A EP 09002892 A EP09002892 A EP 09002892A EP 2224101 A1 EP2224101 A1 EP 2224101A1
Authority
EP
European Patent Office
Prior art keywords
flow
gas turbine
turbine
gas
guiding device
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Withdrawn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
EP09002892A
Other languages
German (de)
English (en)
Inventor
Marc Bröker
Tobias Dr. Buchal
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 EP09002892A priority Critical patent/EP2224101A1/fr
Publication of EP2224101A1 publication Critical patent/EP2224101A1/fr
Withdrawn legal-status Critical Current

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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
    • 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
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle 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
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/72—Application in combination with a steam turbine
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation

Definitions

  • the invention relates to a gas turbine with a flow unit connected downstream of a turbine unit, arranged in a flow medium channel flow guide. It further relates to a gas and steam turbine plant with such a gas turbine.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • guide vanes are also usually arranged between adjacent rotor blade rows and connected to the turbine housing, which are combined into rows of guide blades. These are attached to a usually hollow cylindrical or hollow cone-shaped vane carrier.
  • the gas turbine can be combined in a gas and steam turbine power plant.
  • the flow channel of the gas turbine or arranged in the flow channel exhaust gas diffuser of the gas turbine downstream of a steam boiler is generated in the steam, which can then be used in a steam turbine for generating mechanical energy.
  • the purpose of the exhaust diffuser is to slow down the original flow, at the same time increasing the gas pressure. The diffuser thus converts the kinetic energy of the flow medium into pressure energy.
  • the invention is therefore based on the object to provide a gas turbine of the type mentioned above, which has a very high efficiency with the greatest possible operational safety and durability.
  • the invention is based on the consideration that a particularly safe operation of the gas turbine with simultaneously high efficiency with a particularly uniform and applied flow in the turbine unit downstream areas of the flow channel, in particular in the exhaust gas diffuser, would be achievable. Due to its complexity, this flow can only be predicted very inaccurately during calculations, especially for partial load conditions. This leads to limitations of the actually realizable driving styles. Furthermore, the flow depends strongly on the operation of the gas turbine. An optimization of the flow would thus be possible if the flow-guiding device could be adapted to the respective given operating point and the flow could be influenced in a targeted manner during operation. This can be achieved by the flow guide is pivotable during operation of the gas turbine.
  • the flow-guiding device is arranged in the region of an exhaust gas diffuser of the gas turbine.
  • an adjustable Strömungsleitvorraum at the interface between gas turbine exhaust diffuser and downstream components, the flow of either an exhaust tower, a steam boiler or the afterburner can be optimally adjusted to the operating point during operation.
  • By an adjustability in this area a particularly uniform and applied flow for all operating conditions can be achieved. This vibration excitations are avoided and achieved a particularly high efficiency and a particularly high operational safety of the gas turbine during operation.
  • the flow guiding device comprises a pivot joint and an actuator device provided for aligning the position of the pivot joint.
  • an actuator device can be provided, for example, a servomotor or a hydraulic actuator.
  • the flow guide should advantageously comprise a Strömungsleitgitter with a number of Strömungsleitblechen.
  • the Strömungsleitgitter should include a cantilevered grid frame on which the Strömungsleitgitter are arranged itself.
  • the frame itself should minimize the free flow cross section as little as possible.
  • the respective flow baffle is arranged perpendicular to the Strömungsleitgitter to ensure optimum management of the flow.
  • the respective flow baffle comprises several, in the flow direction of each other spaced segments.
  • the flow guiding device comprises two Strömungsleitgitter arranged opposite one another in the flow channel.
  • a flow influencing on opposite walls of the flow channel is separately possible and it is achieved a particularly good avoidance of flow separation.
  • the flow guidance device advantageously comprises a number of flow guide gratings connected in series behind one another in the flow channel on the flow medium side.
  • the flow-guiding device comprises a plurality of pivot joints whose pivot axes point in different directions.
  • such a gas turbine is used in a gas and steam turbine plant, since one of the turbine unit flow medium downstream flow guide, which is pivotable during operation of the gas turbine, optimizing the flow of the flow medium in the gas turbine downstream boiler allows.
  • a particularly high efficiency is achieved at the same time particularly high operational safety by avoiding flashback when using afterburner.
  • the advantages achieved by the invention are in particular that achieved by the use of a pivotable in operation of the gas turbine Strömungsleitvorides at the outlet of the gas turbine, a particularly high efficiency of a gas turbine and a gas and steam turbine plant by selectively influencing and optimizing the gas flow for a variety of operating conditions becomes.
  • the use of an adjustable Strömungsleitgitters in the region of the exhaust diffuser namely the flow of the exhaust tower or the boiler or the afterburner can be optimally adjusted during operation to the operating point.
  • the flow is also distributed more evenly, which in particular flow separation on outer walls are avoided. Due to the pivoting of the flow-guiding device, a change in the flow during operation and thus a readjustment in the case of different operating modes of the gas turbine is possible.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine unit 6 for driving the compressor 2 and a generator, not shown, or a working machine. These are the turbine unit 6 and the compressor 2 are arranged on a common turbine shaft 8, also referred to as a turbine rotor, with which the generator or the working machine is also connected, and which is rotatably mounted about its turbine axis 9.
  • the running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the turbine unit 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine unit 6 comprises a number of stationary vanes 14, which are also attached in a donut-like manner to a vane support 16 of the turbine unit 6 to form rows of vanes.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine unit 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18 which is arranged to fix the respective vane 14 to a vane support 16 of the turbine unit 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine unit 6.
  • Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 19, also referred to as a blade root.
  • each ring segment 21 is arranged on a guide blade carrier 16 of the turbine unit 6 respectively.
  • the outer surface of each ring segment 21 is also exposed to the hot, the turbine unit 6 flowing through the working medium M and spaced in the radial direction from the outer end of the opposed blades 12 by a radial gap.
  • the ring segments 21 arranged between adjacent guide blade rows serve in particular as cover elements which protect the guide blade carrier 16 or other housing built-in components from thermal overload by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is designed in the embodiment as a so-called annular combustion chamber, in which a plurality of circumferentially around the turbine shaft 8 arranged around burners 10 open into a common combustion chamber space.
  • the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8 around.
  • FIG. 2 and 3 each show a gas turbine 1 with a number of downstream in the flow channel 24 components.
  • the turbine unit 6 of the gas turbine 1 is followed by an exhaust gas diffuser 26, which has a widening pipe mouth in which the original flow slows down, at the same time increasing the gas pressure.
  • the exhaust gas diffuser 26 is further followed by a steam boiler 28, which comprises a number of evaporator and superheater tubes and in which the residual temperature of the working medium M is used from the gas turbine 1 for generating superheated steam for a steam turbine. After the utilization of the residual heat in the steam boiler 28, the working medium M finally flows into an exhaust stack 30.
  • a steam boiler 28 which comprises a number of evaporator and superheater tubes and in which the residual temperature of the working medium M is used from the gas turbine 1 for generating superheated steam for a steam turbine.
  • the flow of the working medium M should abut against the inner wall 32 of the exhaust gas diffuser 26.
  • a flow-guiding device 34 is arranged in the region of the exhaust gas diffuser 26, which is arranged in the FIG. 2 a Strömungsleitgitter 36 includes, which is pivotally mounted on the inner wall 32 by means of a pivot joint 38 which is controlled by an actuator device, not shown in detail. Perpendicular to the Strömungsleitgitter 36 while a plurality of Strömungsleitblechen 40 are arranged, which comprise a plurality of spaced apart in the flow direction segments to avoid unsteady flow separation zones. The flow guide plates 40 and the Strömungsleitgitter 36 thereby influence the flow direction of the working medium M in the region of the exhaust diffuser 26th
  • the position of the flow guiding device in the exhaust gas diffuser 26 can be influenced in a targeted manner.
  • the flow-guiding device 34 is pivoted in the downstream direction, the flow-guiding plates 40 lead to a flow deflection and thus to a more uniform distribution of the flow in the downstream component. As a result, in particular flow separations on the inner walls 32 are avoided.
  • the flow guiding device 34 comprises two flow guide gratings 36, which are arranged pivotably on opposite inner walls 32 and have a number of flow guide plates 40.
  • the flow guide gratings 36 can be pivoted a few degrees both upstream and downstream.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
EP09002892A 2009-02-27 2009-02-27 Turbine à gaz Withdrawn EP2224101A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09002892A EP2224101A1 (fr) 2009-02-27 2009-02-27 Turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09002892A EP2224101A1 (fr) 2009-02-27 2009-02-27 Turbine à gaz

Publications (1)

Publication Number Publication Date
EP2224101A1 true EP2224101A1 (fr) 2010-09-01

Family

ID=41435386

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09002892A Withdrawn EP2224101A1 (fr) 2009-02-27 2009-02-27 Turbine à gaz

Country Status (1)

Country Link
EP (1) EP2224101A1 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH175761A (de) * 1932-12-17 1935-03-15 Spontan Ab Dampf- oder Gasturbine.
SU487242A1 (ru) * 1973-10-08 1975-10-05 Ленинградский Ордена Ленина Политехнический Институт Им.М.И. Калинина Выхлопной патрубок цилиндра низкого давлени паровой турбины
DE2953333C1 (de) * 1978-11-27 1983-11-24 Char'kovskij politechničeskij institut imeni V.I. Lenina, Char'kov Turbinenabdampfstutzen
EP0538918A1 (fr) * 1991-10-24 1993-04-28 Philip Rijk Koudijs Système de décharge pour gases de combustion
US5301500A (en) * 1990-07-09 1994-04-12 General Electric Company Gas turbine engine for controlling stall margin
US5329970A (en) * 1990-09-17 1994-07-19 Wes Technology Inc. Diverter valves
EP0863364A2 (fr) * 1997-03-07 1998-09-09 ABB Combustion Engineering S.p.A. Chaudière de récupération avec canal divergent
US20080063516A1 (en) * 2006-09-08 2008-03-13 Siemens Power Generation, Inc. Adjustable turbine exhaust flow guide and bearing cone assemblies
EP1970539A1 (fr) * 2007-03-13 2008-09-17 Siemens Aktiengesellschaft Agencement de diffuseur

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH175761A (de) * 1932-12-17 1935-03-15 Spontan Ab Dampf- oder Gasturbine.
SU487242A1 (ru) * 1973-10-08 1975-10-05 Ленинградский Ордена Ленина Политехнический Институт Им.М.И. Калинина Выхлопной патрубок цилиндра низкого давлени паровой турбины
DE2953333C1 (de) * 1978-11-27 1983-11-24 Char'kovskij politechničeskij institut imeni V.I. Lenina, Char'kov Turbinenabdampfstutzen
US5301500A (en) * 1990-07-09 1994-04-12 General Electric Company Gas turbine engine for controlling stall margin
US5329970A (en) * 1990-09-17 1994-07-19 Wes Technology Inc. Diverter valves
EP0538918A1 (fr) * 1991-10-24 1993-04-28 Philip Rijk Koudijs Système de décharge pour gases de combustion
EP0863364A2 (fr) * 1997-03-07 1998-09-09 ABB Combustion Engineering S.p.A. Chaudière de récupération avec canal divergent
US20080063516A1 (en) * 2006-09-08 2008-03-13 Siemens Power Generation, Inc. Adjustable turbine exhaust flow guide and bearing cone assemblies
EP1970539A1 (fr) * 2007-03-13 2008-09-17 Siemens Aktiengesellschaft Agencement de diffuseur

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