EP2634382A1 - Turbine à gaz dotée d'un diffuseur de gaz d'échappement et procédé de fonctionnement d'une turbine à gaz - Google Patents

Turbine à gaz dotée d'un diffuseur de gaz d'échappement et procédé de fonctionnement d'une turbine à gaz Download PDF

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Publication number
EP2634382A1
EP2634382A1 EP12157283.8A EP12157283A EP2634382A1 EP 2634382 A1 EP2634382 A1 EP 2634382A1 EP 12157283 A EP12157283 A EP 12157283A EP 2634382 A1 EP2634382 A1 EP 2634382A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
gas turbine
turbine
blow
annular
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Withdrawn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
EP12157283.8A
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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 EP12157283.8A priority Critical patent/EP2634382A1/fr
Publication of EP2634382A1 publication Critical patent/EP2634382A1/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Withdrawn legal-status Critical Current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
    • F01D25/305—Exhaust heads, chambers, or the like with fluid, e.g. liquid injection

Definitions

  • the invention relates to a gas turbine with a subsequent to a turbine unit exhaust diffuser, the diffuser channel is bounded by a conical wall and in the at least one pipe comprehensive Abblase effet outflow ends, whose inflow-side end is connected to a compressor of the gas turbine. Furthermore, the invention relates to a method for operating such a gas turbine.
  • Gas turbines and their modes of operation are well known from the widely available state of the art. They always include an exhaust gas diffuser as part of an exhaust gas line, through which the exhaust gas flowing out of the gas turbine can be continued. The exhaust gas is either led to a chimney, if the gas turbine for single operation, called in English Simple Cycle, is provided.
  • CCGT Combined Cycle
  • the exhaust route leads the exhaust gas to a boiler, with the help of which the thermal energy contained in the exhaust gas is converted into steam for a steam turbine.
  • the operating point of the exhaust diffuser depends primarily on its volume flow. This is known to be mainly influenced by the ambient temperature, the compressor inlet guide blade position and the firing temperature.
  • the exhaust diffuser should meet several requirements: Firstly, a maximum pressure recovery is required for maximum efficiency at the design point. At the same time, the efficiency should drop only slightly at the distance from the design point, if possible. On the other hand, it should have no instationary operating behavior, what else could affect the mechanical integrity of the power plant by vibration excitation. In addition, it should have the most uniform possible speed distribution at the outlet to achieve a good boiler efficiency. Equally important is the avoidance of flip-flop effects when changing the operating point during deep part-load operation. Finally, the exhaust diffuser should also be small-sized and therefore inexpensive.
  • the object of the invention is therefore to provide a gas turbine with a subsequent to a turbine unit exhaust diffuser, which can counteract the problems mentioned in the prior art.
  • the gas turbine is equipped with an exhaust gas diffuser whose diffuser channel is delimited by a conical wall and in which at least one pipe comprehensive Abblase effet outflow ends, whose einström workedes end is connected to a compressor of the gas turbine, wherein a plurality of pipes common annular channel ends, which annular channel opens downstream annular gap-shaped in the boundary wall of the diffuser.
  • the annular channel includes in the mouth region with the boundary wall of the exhaust gas diffuser an angle less than 20 °.
  • the mouth region is designed to be almost parallel to the boundary wall.
  • annular gap is located immediately downstream of the blades of a last turbine stage of the turbine unit.
  • the axial position of the injection into the exhaust gas diffuser has thus been shifted far upstream.
  • the additional benefit is to use an already existing gap between the turbine outlet and the exhaust diffuser inlet for feeding the blow-off air.
  • This is particularly advantageous in the partial load case of the gas turbine, as only during the gap is to block by blowing air against a collection of exhaust gas, but not at full load. By blocking the column, it is avoided that exhaust gas from the hot gas path enters the gas turbine housing in said operating state. This prevents the premature aging of the components involved in the gap and arranged outside thereof and thus obtains their predicted lifetime.
  • the invention will be explained in more detail with reference to a single figure.
  • the single embodiment shows a gas turbine in a longitudinal section.
  • the Axialturbover Noticer 18 includes a ring-shaped compressor duct with cascading successively compressor stages of blade and Leitschaufelkränzen.
  • the rotor blades 14 arranged on the blades 27 are located with their free-ending blade tips of an outer channel wall of the compressor passage opposite.
  • the compressor duct discharges via a compressor outlet diffuser 36 in a plenum 38.
  • the annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas duct 30 of the turbine unit 24. In the turbine unit 24 four successive turbine stages 32 are arranged.
  • a generator or a working machine (each not shown) is coupled.
  • the axial turbocharger 18 draws in ambient air 34 through the intake housing 16 as a medium to be compressed and compresses it.
  • the compressed air is guided through the compressor outlet diffuser 36 into the plenum 38, from where it flows into the burner 22.
  • Fuel also passes into the combustion space 28 via the burners 22.
  • the fuel is burned to a hot gas M with the addition of the compressed air.
  • the hot gas M then flows into the hot gas duct 30, where it relaxes to perform work on the turbine blades of the turbine unit 24.
  • the energy released during this time is absorbed by the rotor 14 and used on the one hand to drive the axial turbocharger 18 and on the other hand to drive a working machine or electric generator.
  • the turbine exhaust manifold 29 connects to the turbine outlet housing 26 of the gas turbine 10. Both components are part of the gas turbine exhaust diffuser 21. Downstream of the turbine exhaust manifold 29, a not further shown exhaust gas system is provided. This and the gas turbine exhaust diffuser 21 thereby form the exhaust gas diffuser system.
  • the turbine outlet housing 26 is formed by an outer boundary wall 23 and the turbine exhaust manifold 29 is formed by an outer boundary wall 40.
  • an annular channel 31 is provided on the outwardly facing surface of the boundary wall 40.
  • the annular channel 31 extends along the entire circumference of the boundary 40 and is almost completely separated from the diffuser channel 38 via a partition wall 33, which is part of the boundary wall 40.
  • the annular channel 31 has laterally an annular opening 43 which opens into an annular gap 35 arranged in the boundary wall 40.
  • a blow-off line 41 opens into the annular channel 31.
  • the blow-off line 41 comprises three pipes, of which only one pipe 42 is shown. It can also be provided more than three or fewer pipes.
  • the pipes, not shown, are distributed along the circumference of the gas turbine 10.
  • each pipeline also a valve is provided as an actuator 46 for closing and partial or complete opening of the pipes.
  • All pipes 42 connect the compressor 18 or the plenum 38 with the annular channel 31, to this - viewed along the circumference - selectively supplying blow-off air.
  • a further blow-off in an analogous configuration may be provided downstream of the last turbine blade row 47. This is in FIG. 1 indicated only by the annular channel 48.
  • the invention relates to a gas turbine 10 having a subsequent to a turbine unit 24 exhaust diffuser 21, the diffuser channel 38 is bounded by a conical wall 23 and in the at least one pipe 42 comprehensive Abblasetechnisch 41 outflow ends, whose inflow-side end with a compressor 18th the gas turbine 10 is connected.
  • a plurality of pipes 42 in a common annular channel 31, 48 ends, said annular channel 31, 48 downstream ringpaltförmig in the boundary wall 23, 40 opens.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP12157283.8A 2012-02-28 2012-02-28 Turbine à gaz dotée d'un diffuseur de gaz d'échappement et procédé de fonctionnement d'une turbine à gaz Withdrawn EP2634382A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12157283.8A EP2634382A1 (fr) 2012-02-28 2012-02-28 Turbine à gaz dotée d'un diffuseur de gaz d'échappement et procédé de fonctionnement d'une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12157283.8A EP2634382A1 (fr) 2012-02-28 2012-02-28 Turbine à gaz dotée d'un diffuseur de gaz d'échappement et procédé de fonctionnement d'une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2634382A1 true EP2634382A1 (fr) 2013-09-04

Family

ID=45833118

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12157283.8A Withdrawn EP2634382A1 (fr) 2012-02-28 2012-02-28 Turbine à gaz dotée d'un diffuseur de gaz d'échappement et procédé de fonctionnement d'une turbine à gaz

Country Status (1)

Country Link
EP (1) EP2634382A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3690786A (en) * 1971-05-10 1972-09-12 Westinghouse Electric Corp Low pressure end diffuser for axial flow elastic fluid turbines
US20090257868A1 (en) * 2008-04-09 2009-10-15 Giusto Fonda-Bonardi Diffuser
US20110056179A1 (en) * 2009-06-02 2011-03-10 John Orosa Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3690786A (en) * 1971-05-10 1972-09-12 Westinghouse Electric Corp Low pressure end diffuser for axial flow elastic fluid turbines
US20090257868A1 (en) * 2008-04-09 2009-10-15 Giusto Fonda-Bonardi Diffuser
US20110056179A1 (en) * 2009-06-02 2011-03-10 John Orosa Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow

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