EP2508711A1 - Palier de turbine axial doté d'un dispositif de sortie d'air et turbine de gaz dotée du palier de turbine axial ainsi que procédé de fonctionnement du palier de turbine axial - Google Patents

Palier de turbine axial doté d'un dispositif de sortie d'air et turbine de gaz dotée du palier de turbine axial ainsi que procédé de fonctionnement du palier de turbine axial Download PDF

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Publication number
EP2508711A1
EP2508711A1 EP11161498A EP11161498A EP2508711A1 EP 2508711 A1 EP2508711 A1 EP 2508711A1 EP 11161498 A EP11161498 A EP 11161498A EP 11161498 A EP11161498 A EP 11161498A EP 2508711 A1 EP2508711 A1 EP 2508711A1
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EP
European Patent Office
Prior art keywords
gas
turbine stage
vane
axial turbine
blow
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Withdrawn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
EP11161498A
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German (de)
English (en)
Inventor
Boris Dobrzynski
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 EP11161498A priority Critical patent/EP2508711A1/fr
Publication of EP2508711A1 publication Critical patent/EP2508711A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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

Definitions

  • the invention relates to an axial turbine stage for a gas turbine and a gas turbine with the axial turbine stage, wherein the axial turbine stage is equipped with a blow-out device, and a method for operating the axial-turbine stage.
  • a gas turbine is coupled, for example, in a power plant for generating electrical energy with a generator and is operated both in partial load operation and in full load operation at the same speed.
  • the power requirements of the gas turbine are typically such that the gas turbine is constructed in an axial fashion.
  • the gas turbine includes a compressor, a combustion chamber, and a turbine, wherein ambient air is drawn and compressed by the compressor, which is heated in the combustion chamber with combustion of a fuel. The heated and compressed air is expanded in the turbine to perform work, which is driven by the resulting excess work the generator.
  • the turbine has at least one turbine stage, which is formed by a row of vanes and a blade row, wherein seen in the main flow direction, the row of vanes upstream of the blade row is arranged.
  • the maximum allowable turbine inlet temperature results from the thermal capacity of the turbine, in particular the turbine stage immediately downstream of the combustion chamber.
  • the turbine inlet temperature and the overall pressure ratio of the gas turbine decrease, compared with the full-load operation of the gas turbine, whereby the thermodynamic efficiency of the gas turbine is lowered disadvantageously in partial load operation.
  • the total mass flow of the main flow through the gas turbine is reduced, thereby disadvantageously differentiating the relative inflow angles of the turbine blades, particularly the turbine blades of the blade row behind the first row of vanes, compared to the inlet angles in the design state. This results in the partial load operation of the gas turbine to a Fehlanströmung the turbine blades, whereby the working implementation is reduced in the turbine blades disadvantageous.
  • the individual stage pressure ratios and thus the overall pressure ratio of the gas turbine are lowered and the exhaust-gas temperature rises while the turbine inlet temperature remains substantially constant.
  • an operating state may occur in which the exhaust gas temperature exceeds a maximum permissible maximum value.
  • An adequate response to this would be to lower the turbine inlet temperature in this part-load operation, so that the exhaust gas temperature is equal to or less than its maximum permissible maximum value, although disadvantageously accompanied by a reduction in the thermodynamic efficiency of the gas turbine.
  • the object of the invention is to provide a Axialturbinencut for a gas turbine and a gas turbine with the Axialturbinentake and methods for operating the Axialturbinencut, wherein axial turbine stage and the gas turbine in the partial load range have a high thermodynamic efficiency.
  • the axial turbine stage according to the invention for a gas turbine has a vane and a downstream of the vane arranged Blade on the pressure side in the region of the trailing edge of the guide vane Ausblasegas in the main flow of Axialturbinencut is blown out, wherein the Ausblase boots has an adjusting device with which the Ausblaserate is adjustable in part-load operation such that the effective profile geometry of the vane means the blowby gas is changed, whereby the relative inflow angle of the blade to the relative design flow angle of the blade is equalized.
  • the method according to the invention for operating the axial-flow turbine stage comprises the steps of: operating the gas turbine in partial-load operation; Adjusting the Ausblaserate with the adjusting device such that the effective profile geometry of the guide vane is changed by means of the blow-by gas, whereby the relative inflow angle of the blade is adjusted to the relative design flow angle of the blade.
  • the deflecting effect of the vane is enhanced, compared with the deflecting effect of the vane with no outflow of the blow-by gas in the region of the trailing edge of the vane.
  • the blow-off rate is increased during operation of the gas turbine by blowing out the blow-off gas at the pressure side in the region of the trailing edge of the guide vane into the main flow of the axial turbine stage, as a result of which the deflection effect of the vane increases.
  • the purging takes place between 30% to less than 100% of the profile chord length of the vane.
  • the blow-out device is preferably formed by an inner cavity of the guide vane and at least one blow-off gas outlet opening, which is arranged on the pressure-side in the region of the trailing edge in the guide vane and connects the inner cavity of the vane gas-conducting to the outside.
  • the guide vane has a plurality of Ausblasegasaustrittsö réelleen which are arranged in a row parallel to the trailing edge.
  • the Ausblasegasauseriesö réelleen which are arranged parallel to the trailing edge.
  • the at least one Ausblasegasausbergsö réelle is a slot which is arranged parallel to the trailing edge.
  • the turbine stage preferably has a feed channel which opens into the inner cavity of the guide vane and through which the blow-by gas can be conveyed to the blow-off gas openings via the inner cavity.
  • the feed channel preferably has a throttle valve as the adjusting device, with which the Ausblaserate is controllable.
  • the feed channel preferably has a filter with which the blowby gas can be filtered, wherein the throttle valve is preferably integrated in the filter.
  • the blow-off gas is preferably a cooling gas of the guide vane and preferably a compressor discharge air of the gas turbine.
  • the cooled by the cooling gas cooled vane is designed so that they are in full load operation with supply of a according to sufficiently large mass flow of the refrigerant gas in the design point with a sufficiently long life is operational.
  • the mass flow of the cooling gas is so large that a thermal overload of the vane is prevented by the cooling effect of the cooling gas on the vane.
  • the profile of the guide vane is chosen so that, taking into account the cooling effect by the cooling medium and its aerodynamic influence, the vane meets defined design requirements in the design point.
  • the increase of the Ausblaserate would not be necessary in view of the necessary cooling effect.
  • the increase in the Ausblaserate causes an increase in the deflection of the vane.
  • the relative inflow angle of the blade is adjustable, wherein the guide vane is operated sufficiently cooled.
  • the guide vane is designed in full load operation for a throttled by the throttle valve mass flow of the cooling gas and in partial load operation for a throttled unthrottled by the throttle valve mass flow of the cooling gas.
  • the throttle valve in partial load operation, is preferably operated unthrottled. If, however, the gas turbine is operated at full load, then the throttle valve is throttled to operate.
  • the reduction of the blow-out rate caused thereby should be selected so that both sufficient cooling and a sufficient deflecting effect of the guide blade during operation of the gas turbine are always provided.
  • the Ausblaserate is increased in partial load operation based on a Ausblaserate in full load operation.
  • a gas turbine 1 has a housing 2, in which a compressor (not shown), a combustion chamber 3 and a turbine are arranged, which has a plurality of turbine stages 8, 9. Downstream of the compressor end, a deflection diffuser (not shown) is arranged, which opens into a compressor plenum 5, which is designed as a cavity in the housing 3 and in which the combustion chamber 3 is arranged.
  • a deflection diffuser (not shown) is arranged, which opens into a compressor plenum 5, which is designed as a cavity in the housing 3 and in which the combustion chamber 3 is arranged.
  • ambient air is drawn in by the compressor and compressed to a compressor discharge pressure.
  • the compressor discharge air enters the combustion chamber interior 4 of the combustion chamber 3 and is mixed with a liquid or gaseous fuel. This results in the combustion chamber interior 4, a combustible mixture ignited and is burned in the combustion chamber 3.
  • the combustion in the combustion chamber interior 4 is essentially isobaric.
  • the mixture has a correspondingly caused by the combustion
  • the first turbine stage 8 has a stator blade row 10 and a rotor blade row 12.
  • the vane row 10 of the first turbine stage 8 is formed by a plurality of circumferentially equidistantly arranged, same vanes 11.
  • the blade row 12 of the first turbine stage 8 is formed by an equidistantly arranged around the circumference, the same blades 13.
  • the vanes 11 and the blades 13 are designed in Axialbautician.
  • the vanes 11 are held at their radially outer ends by a vane carrier 14.
  • the rotor blades 13 are each equipped at their radially inner ends with a blade root, which is in a form-fitting engagement with a rotor 15 of the gas turbine 1.
  • Each vane 11 has an airfoil with a trailing edge 16, a leading edge and a suction side (not shown) and a pressure side 18.
  • Each blade 13 has a leading edge 17 which, by design, has a relative design inflow angle 26.
  • the hot gas mixture introduced into the transition duct 7 enters the first turbine stage 8, the hot gas mixture being deflected from the guide blade row 10 and being expanded in the rotor blade row 12 while releasing work.
  • the gas turbine has as an exhaust means an inner space of the guide vane 11 and a number of Ausblase Kunststoffaustrittsö réelleen 24 and a feed channel 20, a filter 21, a throttle valve 22 and a chamber 23 which is disposed immediately radially outside of the vanes 11 and into the interiors of the Guide vanes 11 opens.
  • the radial distance between the chamber 23 and the Verêtrplenum 5 is bridged for each vane 11 with the feed channel 20.
  • the feed channel 20 has the filter 21, in which the throttle valve 20 is integrated.
  • the compressor discharge air flows from the compressor end via the diverting diffuser into the compressor plenum 5, in which the compressor air as the cooling medium (cooling air) is provided. From the Verêtrplenum 5, the cooling air flows via the filter 21 and the throttle valve 20 into the chamber 23 and from there into the interior of each vane 11. From the interior of the vane 11 enters via the Ausblase Kunststoffaustrittsö Maschinenen 24 a Ausblaseluftstrom 25 in the main flow, wherein Operation of the throttle valve 20, an adjustment of the Ausblaserate is possible.
  • the pressure of the cooling air in the chamber 23 results in particular from the cooling air mass flow, which flows through the interior of the guide vane 11 from the chamber 23, the cooling air mass flow, which flows through the filter 21 into the chamber 23, and the Throttle position of the throttle valve 20. From the chamber 23 in the interiors of the vanes 11th
  • the guide vanes 11 have in the region of their trailing edges 16 at their pressure sides 18 in each case a substantially radially extending row of exhaust air outlet openings 24, through which the cooling air flows out of the interior of the guide vanes 11 into the main flow.
  • the deflection effect of the guide vanes 11 is enhanced.
  • the throttled in full load throttle valve 20 is opened, whereby the Ausblaseluftstrom 25 of the cooling air through the Ausblaseluftaustrittsö réelleen 24 increases.
  • the deflection effect of the guide vanes 11 increases.
  • FIGS. 2 and 3 For example, S1 face-to-face cuts of the vane 11 and blade 12 as well as velocity triangles for outflow of the vane are shown.
  • Denoted by the reference numeral 28 is the speed triangle for the full load operating state of the gas turbine 1 and designated by the reference numeral 29, the speed triangle for the partial load operating state of the gas turbine 1 is shown.
  • Reference numeral 26 is the relative design inflow angle of the blade 13 for full load operation Gas turbine 1 and the reference numeral 27, the relative inflow angle of the blade 11 is characterized. With the arrow 25 of the blow-off air flow of the blow-off gas is indicated.
  • the throttle valve 20 is opened, in the extreme case completely open, whereby the mass flow through the blow-out air outlet openings 24 is increased.
  • the deflecting effect of the guide vanes 11 is advantageously increased, with the trailing edges 17 of the guide vanes 13 flowing optimally and the guide vanes 11 being sufficiently cooled.
  • the Ausblaserate is zero, so that the Ausblaseluftstrom from the purge air outlet opening is not present.
  • This results in the partial load operation of the relative inflow angle 27 of the blade 13 is shallower than the relative Auslegungszuströmwinkel 26 of the blade 13, whereby the blade 13 is faulty.
  • the purge air flow 25 is set at the purge rate such that the relative inflow angle 27 of the blade 13 is identical to the relative design inflow angle 26 of the blade 13.
  • the blade 13 is advantageously flowing according to design.
EP11161498A 2011-04-07 2011-04-07 Palier de turbine axial doté d'un dispositif de sortie d'air et turbine de gaz dotée du palier de turbine axial ainsi que procédé de fonctionnement du palier de turbine axial Withdrawn EP2508711A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11161498A EP2508711A1 (fr) 2011-04-07 2011-04-07 Palier de turbine axial doté d'un dispositif de sortie d'air et turbine de gaz dotée du palier de turbine axial ainsi que procédé de fonctionnement du palier de turbine axial

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11161498A EP2508711A1 (fr) 2011-04-07 2011-04-07 Palier de turbine axial doté d'un dispositif de sortie d'air et turbine de gaz dotée du palier de turbine axial ainsi que procédé de fonctionnement du palier de turbine axial

Publications (1)

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EP2508711A1 true EP2508711A1 (fr) 2012-10-10

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EP11161498A Withdrawn EP2508711A1 (fr) 2011-04-07 2011-04-07 Palier de turbine axial doté d'un dispositif de sortie d'air et turbine de gaz dotée du palier de turbine axial ainsi que procédé de fonctionnement du palier de turbine axial

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EP (1) EP2508711A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017204941A1 (fr) * 2016-05-25 2017-11-30 General Electric Company Système pour turbine basse-pression à faible tourbillon
CN109578085A (zh) * 2018-12-26 2019-04-05 中国船舶重工集团公司第七0三研究所 一种通过导叶倾斜减弱涡轮动叶非定常作用力的方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE566224A (fr) *
FR1263010A (fr) * 1960-07-21 1961-06-05 M A N Turbomotoren G M B H Procédé et dispositif pour modifier, dans les machines à écoulement de flaide, la déviation donnée par une grille d'aubes
US3385509A (en) * 1965-12-02 1968-05-28 Snecma Gas turbine engines having contrarotating compressors
US3726604A (en) * 1971-10-13 1973-04-10 Gen Motors Corp Cooled jet flap vane
US3751909A (en) * 1970-08-27 1973-08-14 Motoren Turbinen Union Turbojet aero engines having means for engine component cooling and compressor control
GB2367096A (en) * 2000-09-23 2002-03-27 Abb Alstom Power Uk Ltd Turbocharger arrangement with exhaust gas diverter valve

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE566224A (fr) *
FR1263010A (fr) * 1960-07-21 1961-06-05 M A N Turbomotoren G M B H Procédé et dispositif pour modifier, dans les machines à écoulement de flaide, la déviation donnée par une grille d'aubes
US3385509A (en) * 1965-12-02 1968-05-28 Snecma Gas turbine engines having contrarotating compressors
US3751909A (en) * 1970-08-27 1973-08-14 Motoren Turbinen Union Turbojet aero engines having means for engine component cooling and compressor control
US3726604A (en) * 1971-10-13 1973-04-10 Gen Motors Corp Cooled jet flap vane
GB2367096A (en) * 2000-09-23 2002-03-27 Abb Alstom Power Uk Ltd Turbocharger arrangement with exhaust gas diverter valve

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017204941A1 (fr) * 2016-05-25 2017-11-30 General Electric Company Système pour turbine basse-pression à faible tourbillon
CN109154195A (zh) * 2016-05-25 2019-01-04 通用电气公司 用于低涡旋低压涡轮机的系统
CN109578085A (zh) * 2018-12-26 2019-04-05 中国船舶重工集团公司第七0三研究所 一种通过导叶倾斜减弱涡轮动叶非定常作用力的方法
CN109578085B (zh) * 2018-12-26 2021-06-22 中国船舶重工集团公司第七0三研究所 一种通过导叶倾斜减弱涡轮动叶非定常作用力的方法

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