EP2532898A1 - Axialturboverdichter - Google Patents

Axialturboverdichter Download PDF

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Publication number
EP2532898A1
EP2532898A1 EP11169109A EP11169109A EP2532898A1 EP 2532898 A1 EP2532898 A1 EP 2532898A1 EP 11169109 A EP11169109 A EP 11169109A EP 11169109 A EP11169109 A EP 11169109A EP 2532898 A1 EP2532898 A1 EP 2532898A1
Authority
EP
European Patent Office
Prior art keywords
channel
wall
compressor
removal
axial
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Withdrawn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
EP11169109A
Other languages
German (de)
English (en)
French (fr)
Inventor
Dirk Mertens
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
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 EP11169109A priority Critical patent/EP2532898A1/de
Priority to US13/488,540 priority patent/US20120315131A1/en
Priority to JP2012129623A priority patent/JP2012255440A/ja
Priority to CN2012101871763A priority patent/CN102817865A/zh
Publication of EP2532898A1 publication Critical patent/EP2532898A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface

Definitions

  • the invention relates to a Axialturbover emphasizer with an about a rotational axis concentrically arranged annular compressor passage, which is bounded radially outwardly by a channel wall and rotatably mounted in the ringable to a ring rotatable blades about the rotation axis, wherein the free-ending tips of the blades each with gap formation of Channel wall opposite and the channel wall in the axial portion of the tips at least partially a wall structuring (also known as casing treatment) and wherein a removal opening of a removal channel for tapping of a medium flowing in the compressor channel medium is provided in the channel wall.
  • a wall structuring also known as casing treatment
  • the above-described arrangement is for example from the GB 2 158 879 A known.
  • the casing treatment is provided on the casing-side channel wall above an upstream blade row and the bleed-off point is located at a downstream row of blades.
  • a valve is provided in the removal channel in order to tap different quantities of compressor air as a function of the operating state. Both measures allow a degree of regulation of the operation of the compressor for high pressure conditions, without causing unwanted compressor phenomena such as pumps or detachment phenomena (surge).
  • the disadvantage is that the aforementioned embodiment has proven to be inadequate for a partial load operation of a gas turbine.
  • the object of the invention is therefore to provide an axial turbocompressor, in which the operating range is further improved by a more efficient avoidance of undesired compressor phenomena.
  • Another object of the invention is to provide a gas turbine with a Axialturbover participatr invention, which avoids inadmissible emissions especially at part load operation.
  • the invention is provided to settle the removal opening in the wall structuring. It is thus not only the simultaneous application of a casing treatment and the tapping of compressor air within a Axialturboverêtrs proposed, but the combination also takes place locally, namely in the range of a single blade row of Axialturbover confusers. Damming the compressed air and thus an aerodynamically unfavorable high pressure ratio in the subsequent compressor stages can thus be avoided, which largely avoids the emergence of unwanted compressor phenomena. Due to the combination according to the invention, the surge limit of the relevant compressor stage can be adjusted in a particularly simple and operating state-dependent manner.
  • the adjustable in size or shape Casing Treatment not only the setting of the wall structuring, but also serves as an actuator for connecting or disconnecting the removal of compressor air. This also allows a particularly space-saving design.
  • the aforementioned embodiment can be implemented in a particularly simple design if the wall structuring can be changed in size and / or shape by means of a movable insert and the removal opening is located in a side wall of the insert receiving the insert.
  • the insert may be formed as a plug, which can be moved along the recess. Depending on the position of the plug, either the recess is completely closed (for the first operating state), the recess is only partially closed with the removal openings still closed (for the second operating state) or the recess and the removal opening are open (for the third operating state). In this respect, alone by the displacement of the plug along its receiving recess between the three aforementioned operating conditions are switched back and forth in a simple and reliable manner.
  • the removal channel may be connected on the flow output side with a blow-off air system and / or cooling air system.
  • FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section.
  • the gas turbine 10 has inside a rotatably mounted about an axis of rotation 12 rotor 14, which is also referred to as a turbine runner.
  • rotor 14 successively follow an intake housing 16, a Axialturbover Noticer 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetrical mutually arranged burners 22, a turbine unit 24 and an exhaust housing 26.
  • the gas turbine can also be equipped with silo or with tube combustion chambers.
  • the Axialturbover Noticer 18 includes a ring-shaped compressor duct 25 with successively cascaded compressor stages of blade and vane rings.
  • the rotor blades 14 arranged on the blades 27 are with their free-ending blade tips 29 an outer channel wall 42 of the compressor passage 25 opposite.
  • the compressor passage 25 opens 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.
  • four turbine stages 32 connected in series are arranged in the turbine unit 24.
  • 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 process is absorbed by the rotor 14 and on the one hand used to drive the Axialturboverêtrs 18 and on the other hand to drive a working machine or electric generator.
  • At least one wall structuring is provided in the channel wall 42.
  • This wall structuring is in FIG. 1 for the sake of clarity not shown.
  • This wall structuring is furthermore known as a so-called "casing treatment” and is designed, for example, as grooves running continuously in the circumferential direction or distributed over the circumference and extending in the axial direction.
  • the wall structuring is usually provided in an axial section of the compressor duct 25, in which the free-ending tips of rotor blades 27 lie opposite one another with gap formation of the duct wall 42.
  • FIGS. 2 and 3 show now in detail in cross section a section through the channel wall 42 of the compressor duct 25 in the region of a wall structure 44.
  • the wall structuring 44 comprises according to this first embodiment a plurality of radially extending through the channel wall 42 recesses 46. In each recess 46 sits a radially displaceable, in Cross-section T-shaped insert 48. In the recess 46 open two channels laterally. These channels are designed as removal channels 50. Its opening 52 is located in the wall structure 44, ie in the side wall 54 of the recess 46. When pushed inward insert 48, the recess 46 and at the same time the removal openings 52 are completely closed (not shown).
  • the recess 46 is partially opened to activate the aerodynamically effective Wand Wegberichtbericht 44 by the insert 48 from its recess 46, the relevant closure position was moved to the outside.
  • the first opening 52 of the removal channel 50 is exposed, so that at the same time the compressor duct 25 via the recess 46 compressor air removed, ie can be tapped.
  • the in FIG. 3 shown position of the insert 48 are both removal openings 52 of the removal channels 50 exposed.
  • the wall structure 44 is variable in size and / or shape and thereby the removal opening 52 at least partially exposed.
  • FIG. 4 shows a second embodiment of the device according to the invention in a perspective view.
  • the second embodiment in the direction of the compressor channel 25 facing surface of the channel wall 42 are now provided in the circumferential direction endlessly extending grooves 60 along which the tips of the blades, not shown, rotate.
  • a side wall 61 of the grooves 60 open several, uniformly distributed along the circumference removal channels 62, only a few of which are shown schematically.
  • the valve system for opening and / or closing the removal of compressor air is nevertheless not formed by movable inserts, but designed as a downstream system.
  • the extraction channels 62 can of course also be distributed unevenly.
  • the wall structure 44 is formed as extending in the axial direction, evenly distributed over the circumference of the channel wall 42 grooves 64 which are located in a circumferentially rotatable insert 45, which arranged in a channel wall 42, corresponding to the insert 45 recess 47 is settled.
  • the removal openings 52 of the removal channels 50 are arranged between the grooves 64 webs 49 of the insert 45.
  • FIGS. 6 and 7 show the FIGS. 6 and 7 in each case partial perspective representation.
  • FIG. 6 shows a channel wall 42 having a groove 66 which is endless in the circumferential direction, in which a radially displaceable insert 68 for opening and closing the wall structuring 44 and the removal opening 52 arranged in the groove side wall 70 is located.
  • the removal opening 52 is closed by the insert 68.
  • the removal opening 52 is open.
  • the present invention proposes an axial turbocompressor 18 or a gas turbine 10 with an annular compressor channel 25 arranged concentrically around a rotation axis 12, which is bounded radially on the outside by a channel wall 42 and in the ringable rotor blades 29 which can be combined to form a ring around the axis of rotation 12 are arranged rotatably mounted.
  • the free-ending tips 29 of the blades 29 are each with gap formation of the channel wall 42 opposite, wherein in the channel wall 42 itself in the axial portion of the tips 29 at least partially a wall structuring 44 is provided.
  • a removal opening 52 of a removal channel 50 for tapping and removal of air flowing in the compressor passage 25 is provided, which is located according to the invention in the wall structure 44.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP11169109A 2011-06-08 2011-06-08 Axialturboverdichter Withdrawn EP2532898A1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP11169109A EP2532898A1 (de) 2011-06-08 2011-06-08 Axialturboverdichter
US13/488,540 US20120315131A1 (en) 2011-06-08 2012-06-05 Axial turbocompressor
JP2012129623A JP2012255440A (ja) 2011-06-08 2012-06-07 軸流式ターボ圧縮機
CN2012101871763A CN102817865A (zh) 2011-06-08 2012-06-07 轴流式涡轮压缩机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11169109A EP2532898A1 (de) 2011-06-08 2011-06-08 Axialturboverdichter

Publications (1)

Publication Number Publication Date
EP2532898A1 true EP2532898A1 (de) 2012-12-12

Family

ID=44872640

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11169109A Withdrawn EP2532898A1 (de) 2011-06-08 2011-06-08 Axialturboverdichter

Country Status (4)

Country Link
US (1) US20120315131A1 (enrdf_load_stackoverflow)
EP (1) EP2532898A1 (enrdf_load_stackoverflow)
JP (1) JP2012255440A (enrdf_load_stackoverflow)
CN (1) CN102817865A (enrdf_load_stackoverflow)

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Publication number Priority date Publication date Assignee Title
EP3023592A1 (de) * 2014-11-20 2016-05-25 Siemens Aktiengesellschaft Diffusor einer thermischen Energiemaschine sowie thermische Energiemaschine
CN108119406B (zh) * 2018-01-11 2020-11-27 南京航空航天大学 轴流压气机周向大间隔小通孔机匣
US11092030B2 (en) 2019-04-18 2021-08-17 Raytheon Technologies Corporation Adaptive case for a gas turbine engine
US11965528B1 (en) 2023-08-16 2024-04-23 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with circumferential movable closure for a fan of a gas turbine engine
US12078070B1 (en) 2023-08-16 2024-09-03 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with sliding doors for a fan of a gas turbine engine
US12085021B1 (en) 2023-08-16 2024-09-10 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with movable closure for a fan of a gas turbine engine
US11970985B1 (en) 2023-08-16 2024-04-30 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with pivoting vanes for a fan of a gas turbine engine
US12018621B1 (en) 2023-08-16 2024-06-25 Rolls-Royce North American Technologies Inc. Adjustable depth tip treatment with rotatable ring with pockets for a fan of a gas turbine engine
US12066035B1 (en) 2023-08-16 2024-08-20 Rolls-Royce North American Technologies Inc. Adjustable depth tip treatment with axial member with pockets for a fan of a gas turbine engine
US12258870B1 (en) * 2024-03-08 2025-03-25 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with slotted array active fan tip treatment for distortion tolerance
US12286936B1 (en) * 2024-05-09 2025-04-29 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with groove array active fan tip treatment for distortion tolerance
US12209541B1 (en) * 2024-05-09 2025-01-28 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with dual slotted array active fan tip treatment for distortion tolerance
US12215712B1 (en) * 2024-05-09 2025-02-04 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with dual grooved array active fan tip treatment for distortion tolerance
US12209502B1 (en) * 2024-06-28 2025-01-28 Rolls-Royce North American Technologies Inc. Active fan tip treatment using rotating drum array with axial channels in fan track liner for distortion tolerance
US12168983B1 (en) * 2024-06-28 2024-12-17 Rolls-Royce North American Technologies Inc. Active fan tip treatment using rotating drum array in fan track liner with axial and circumferential channels for distortion tolerance

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US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
JPS59168296A (ja) * 1983-03-16 1984-09-21 Hitachi Ltd 多段軸流圧縮機のサ−ジング防止装置
GB2158879A (en) 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
EP1013937A2 (en) * 1998-12-23 2000-06-28 United Technologies Corporation Rotor tip bleed in gas turbine engines
EP1413771A1 (fr) * 2002-10-22 2004-04-28 Snecma Moteurs Carter, compresseur, turbine et turbo moteur à combustion comprenant un tel carter

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JP3872966B2 (ja) * 2001-06-29 2007-01-24 株式会社日立プラントテクノロジー 軸流形流体機械
EP1566531A1 (de) * 2004-02-19 2005-08-24 Siemens Aktiengesellschaft Gasturbine mit einem gegen Auskühlen geschützten Verdichtergehäuse und Verfahren zum Betrieb einer Gasturbine
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FR2882112B1 (fr) * 2005-02-16 2007-05-11 Snecma Moteurs Sa Prelevement en tete des roues mobiles de compresseur haute pression de turboreacteur
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Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
JPS59168296A (ja) * 1983-03-16 1984-09-21 Hitachi Ltd 多段軸流圧縮機のサ−ジング防止装置
GB2158879A (en) 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
EP1013937A2 (en) * 1998-12-23 2000-06-28 United Technologies Corporation Rotor tip bleed in gas turbine engines
EP1413771A1 (fr) * 2002-10-22 2004-04-28 Snecma Moteurs Carter, compresseur, turbine et turbo moteur à combustion comprenant un tel carter

Also Published As

Publication number Publication date
JP2012255440A (ja) 2012-12-27
US20120315131A1 (en) 2012-12-13
CN102817865A (zh) 2012-12-12

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