EP1503046A2 - Dispositif de séparation de particules étrangères contenues dans des fluides de refroidissement d'aubes mobiles d'une turbine - Google Patents

Dispositif de séparation de particules étrangères contenues dans des fluides de refroidissement d'aubes mobiles d'une turbine Download PDF

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Publication number
EP1503046A2
EP1503046A2 EP04103026A EP04103026A EP1503046A2 EP 1503046 A2 EP1503046 A2 EP 1503046A2 EP 04103026 A EP04103026 A EP 04103026A EP 04103026 A EP04103026 A EP 04103026A EP 1503046 A2 EP1503046 A2 EP 1503046A2
Authority
EP
European Patent Office
Prior art keywords
cooling air
radially
flow
deflection unit
nozzle
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Withdrawn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
EP04103026A
Other languages
German (de)
English (en)
Other versions
EP1503046A3 (fr
Inventor
Reinhard Fried
Bernhard Prof. Dr. Weigand
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1503046A2 publication Critical patent/EP1503046A2/fr
Publication of EP1503046A3 publication Critical patent/EP1503046A3/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • the invention relates to a device for separating foreign particles from the blades of a turbine supplied cooling air, in particular for a Gas turbine arrangement, in which the cooling air medium or directly via stationary Nozzle units one between wall parts of a turbine stator and a rotating wheel disc formed annular space as directed in the circumferential direction Cooling air flow can be supplied, wherein the annulus in the wheel disc arranged channels for the supply of cooling air into the blades in combination is, and within the annulus or the annulus one-sided limiting one Deflection unit is provided, with the emerging from the nozzle units Cooling air before entering the channels on one side is deflected so that foreign particles spun into a radially outer part of the annulus and together with a sealing air portion of the supplied cooling air from the annulus deposited become.
  • a generic separation device for foreign particles from a Cooling air flow, for cooling purposes of a turbine blade, preferably a Gas turbine plant is supplied, can be found in EP 0 690 202 B1.
  • cooling air via stationary swirl nozzles one between wall parts the turbine stator and an impeller limited annular space for training a circumferentially extending within the annulus Vortex flow supplied.
  • the swirl nozzles each have a tangential Orientation in the circumferential direction of its arrangement within the turbine stator, wherein the individual nozzle axes in the respective tangential plane oblique to Rotation axis of the rotor assembly to form a swirl flow within of the annulus, are employed.
  • the swirl nozzles in the flow direction within the annulus is arranged downstream of a cross-sectionally L-shaped baffle provided, on which preferably radially directed to the rotor assembly, longer longitudinal leg, the cooling air after exiting the swirl nozzles vertically occurs and is deflected radially outward.
  • a cross-sectionally L-shaped baffle provided, on which preferably radially directed to the rotor assembly, longer longitudinal leg, the cooling air after exiting the swirl nozzles vertically occurs and is deflected radially outward.
  • the foreign particle enrichment in the radial outwardly directed partial air flow is due to acting on the foreign particles Centrifugal force ago, which extends through the circumferentially propagating Swirl flow forms after passing through the swirl nozzle openings.
  • relatively high-mass foreign particles with the in this document but can not be ruled out be that light and smaller dust or foreign particles from the radially to directed inside cooling air flow for further cooling of the turbine blade be carried along.
  • the invention has for its object to provide a device for separating Foreign particles from the blades of a turbine supplied cooling air after form the preamble of claim 1 such that it with as possible technically simple and cost-effective measures is possible in the Turbine blades inflowing cooling air preferably completely but at least largely free of foreign particles.
  • the device for the separation of foreign particles from the the blades of a turbine supplied cooling air in particular for a Gas turbine arrangement, in which the cooling air medium or directly via stationary Nozzle units one between wall parts of the turbine stator and a rotating wheel disc formed annular space as directed in the circumferential direction Cooling air flow can be fed and the annulus with in the wheel disc arranged channels for the supply of cooling air into the blades in combination is, wherein within the annulus or the annulus bounding one side a deflection unit is provided, with which emerging from the nozzle units Cooling air before entering the channels on one side is deflected so that foreign particles spun into a radially outer part of the annulus and together with a sealing air portion of the supplied cooling air from the annulus deposited be further developed such that the deflection unit a surface area on which the cooling air flow passing through the nozzle unit impinges, through which the cooling air flow at an angle ⁇ > 90 ° radially outward is distractible.
  • a first solution variant a fixedly connected to the Turbinenstatorü deflection unit, in which the cooling air flow exiting as jet units nozzle units the radial direction of the rotor assembly perpendicularly intersecting flow direction has - although the channel longitudinal axes of the individual nozzle units for Imprinting a circumferential in the circumferential direction within the annular space Swirl flow are arranged inclined relative to the rotor axis -.
  • the inclination is selected relative to the radial direction of the rotor assembly such that a integral radial outward deflection of the cooling air flow he follows.
  • a preferred embodiment of the deflection unit sees one of the nozzle units facing concave surface contour before, whose surface curvature at least in the area of the area to which the cooling air flow impinges directly, is described by tangential planes, with the axially directed flow component emerging from the nozzle units Cooling air flow include an angle ⁇ of> 90 °.
  • the deflection unit one in the annulus free-ending contour which is for the radially outwardly deflected cooling air flow serves as a stall contour, so that the offset with foreign particles cooling air directly and without further flow obstacles to the radially outer Labyrinthdichtung passes through the interspersed with foreign particles cooling air in the hot gas flow or operating current of the gas turbine plant occurs.
  • a separation of a nearly completely cleaned of foreign particles cooling air takes place in a conventional manner by providing a passage opening between the outline of the deflection unit, which terminates freely as a demolition contour, and a web of the Wheel disc, as in detail also from those shown below Embodiments can be seen.
  • the inventively designed deflection is thus characterized by the special design of the nozzle units facing surface area, in the simplest case by a rectilinear, in the above manner distinguished inclined surface section.
  • To the optimized Flow guide however, have continuously curved concave Surface curvatures proved by the flow losses due to local occurring accumulation effects within the flow guide, are reducible.
  • Another embodiment provides, the channel longitudinal axis of the nozzle units Arranged radially inclined, so that the already from the nozzle units exiting cooling air flow directed radially outward Has flow component. Also in this case, the area of the Deflection unit, on which the cooling air flow impinges, parallel or inclined to Radial direction to be oriented so that the channel longitudinal axis with the Area includes a radially outwardly open angle ⁇ > 90 °.
  • the deflection unit itself is in This case is designed as a ring element and sees in its radially outer Area, preferably distributed in the circumferential direction equal to a plurality of Passage openings in front of the branch of foreign particles cleaned cooling air serve for forwarding into the cooling channels of the wheel disc and the so connected turbine blade.
  • the deflection unit includes together Wall parts of the Turbinenstatorü a kind of annular chamber in the sense of A separation chamber in which the dust or foreign particles from the for cooling purposes of Turbine blade supplied cooling air to be separated.
  • the nozzle units each one Nozzle channel with a flow direction of the cooling air flow determining Channel longitudinal axis provide, which is inclined radially so that the Nozzle channel passing cooling air flow is directed radially outward.
  • the Annular chamber is at least two openings with the annulus connected by the wall parts of the turbine stator and the rotating Wheel disc is limited.
  • One of the at least two passage openings is between the deflection unit and the turbine stator unit radially outward lying and the other arranged radially inside, wherein the channel longitudinal axis of the nozzle unit in Escape is arranged with the radially outer passage opening.
  • Fig. 1 shows a longitudinal section through a turbine stator 1 with a, with this in fixed connection stationary vane 2 and one around the rotor axis R rotatably mounted wheel disc 3 with an attached thereto Turbine blade 4.
  • enclosed volume 5 passes from an unillustrated Compression unit Cooling air that is contaminated with foreign particles, such as dust particles, is offset. Specifically, it is the one supplied by the compression unit Separate cooling air from the foreign particles and the cleaned cooling air to the other Cooling of the blade 4 in the corresponding cooling channels provided for this purpose. 6 within the wheel disc 3, with a corresponding within the blade 4 are provided for cooling purposes provided hollow chamber system to lead.
  • cooling air For separating the foreign particles from that of the compression unit supplied cooling air passes the cooling air from the volume 5 via as swirl nozzles trained nozzle units 7 in one of wall parts of the turbine stator 1 and the rotating wheel disc 3 limited annular space 8, which also radially outward by projecting webs of the guide 2 and 4 bucket in the manner of a Labyrinth seal 13 and radially inside lying through corresponding webs of the Turbinenstators 1 and the wheel disc 3, also in the form of a labyrinth seal is limited.
  • a deflection unit 9 is provided which is fixed to the Turbine stator 1 is connected.
  • the deflection unit 9 is an annular component formed and has a substantially angled profile-like cross section, the a lower connecting web 10 provides that in a corresponding protruding fastening groove protrudes inside the turbine stator 1.
  • the deflection unit 9 provides a surface area 11, to which the through Nozzle unit 7 passing cooling air flow impinges, wherein the surface area 11 is inclined relative to the flow direction of the cooling air flow, that the cooling air flow is deflected outwards by an angle ⁇ > 90 °. To this Way undergoes the passing through the nozzle units 7 cooling air flow in addition all foreign particles containing in this radially outwardly directed Deflection. Thus, any foreign particle deposits between the Nozzle unit 7 and the surface of the radially inner connecting web 10th the deflection unit 9 avoided.
  • the nozzle units 7 have channel longitudinal axes 7 '. although oriented perpendicular to the radial direction, but according to Detail display (see double-arrow illustration) a tangential component to the Inducing a circumferentially within the annular space 8 itself have spreading swirl flow.
  • the nozzle contour 7 facing surface contour of the deflection unit 9 is in shown embodiment formed as a concave curved surface, the in Overflow direction provides a free-ending contour 12, for the radially after outwardly directed flow flow is designed as a flow separation edge.
  • the one with the foreign particles offset flow flow also referred to as the sealing air fraction, thus passes through the radially outer labyrinth seal 13 in the Working channel of the turbine arrangement.
  • a passage opening 14 is provided, through which one of Foreign particles purified cooling air fraction is diverted.
  • the embodiment shown in Fig. 2 is similar except the spatial Position of the channel longitudinal axis of the nozzle unit 7 to that shown in Fig. 1 Embodiment.
  • the channel longitudinal axes 7 ' are each individual nozzle unit 7 additionally inclined radially outward, so that the cooling air flow emerging from the nozzle units 7 in the annular space 8 already before coming into contact with the respective surface area 11 of the deflection unit 9 receives a radially outward flow component.
  • the area 11 on which the cooling flow after passing through the Nozzle unit 7 impinges directly inclined so that the cooling flow around a Angle ⁇ > 90 ° is deflected radially outward.
  • the Nozzle units predetermined radially directed tilt it is possible, even in the Difference to the concave curved in Fig. 2, the nozzle unit 7 facing Surface of the deflection unit 9 to provide an alternative trained deflecting unit, which has only one surface area extending parallel to the radial direction.
  • the deflection unit it would be possible to form the deflection unit as a rectangular L-profile.
  • a deflection unit 9 the fixed with the rotating wheel disc 3 is connected.
  • the arrangement corresponds to the Nozzle units 7 within the turbine stator 1 according to the embodiment It is through the obliquely radially outwardly directed cooling channel longitudinal axis 7 ' possible to form the surface area 11 of the deflection unit 9 in a straight line and at the same time to ensure that the emerging from the nozzle units 7 Cooling air flow is deflected completely radially outward.
  • the fixed with its radially outer region with the web 15 of the wheel disc 3 connected deflection unit 9 has near the web 15 through openings 14, by the cooling air for further cooling from the sealing air portion, over the Labyrinth seal 13 enters the working channel of the turbine assembly, is branched off.
  • the flow from the passage opening 14 repellent Web 16 is provided, according to the detailed representation in Fig. 3, the particle flow (dashed line with dots) from the passage opening 14 is rejected, whereas Foreign particle-free cooling air (solid thick line in detail) by the passage opening 14 passes.
  • Deflection unit 9 By the relative to the turbine stator 1 rotatably arranged Deflection unit 9 is radially inwardly between the turbine stator 1 and the Deflection unit 9, a light intermediate gap 14 'provided by the also Cooling air for further cooling of the blade 4 passes.
  • FIG. 4 and 5 show a comparison with FIG. 3 improved embodiment also firmly connected to the rotating wheel disc 3 deflection units.
  • 9 Fig. 4 shows an arrangement with a radial direction perpendicular cuttingdekanall Kunststoffsachse 7 ', whereas in Fig. 5, an embodiment with a radially outwardly inclined cooling channel longitudinal axis 7 'is shown.
  • the deflection unit 9 has one, which consists of the nozzle unit 7 exiting cooling air flow radially deflecting outward, concave formed surface area 11.
  • the deflecting unit 9 faces the nozzle unit 7 rib-like elements 17 before, as in particular with reference emerge in Fig. 6b in detail.
  • the rib-like elements 17 each have an oriented perpendicular to the axis of rotation of the wheel disc 3 surface, through the reaching into the annular space 8 cooling air in rotation in the circumferential direction is offset.
  • rib-like elements 17 are equidistant from each other along the surface area 11 of the deflection unit 9 as shown in Fig. 6b intended.
  • two adjacent to each other close rib-like elements 17 a passage opening 14 a.
  • Fig. 7 serves to describe a further alternative, inventive Device for separating foreign particles from the blades of a Turbine feedable cooling air, preferably for a gas turbine plant.
  • Fig. 7a serves to describe a known prior art, the provides a turbine stator 1, the axially to a not shown Rotor arrangement of a rotating wheel disc 3 with corresponding blade 4 is arranged.
  • compression unit for the supply of cooling air into a volume 5, from the cooling air exits via a nozzle unit 7 in an annular chamber 18.
  • the Nozzle unit 7 is formed corresponding to that nozzle unit, for example is described with reference to the embodiment in Fig. 1, i. the through the nozzle unit 7 in the annular chamber 18 exiting cooling air is spreading in this as circumferentially rotating swirl flow out.
  • the nozzle unit 7 a nozzle channel 71 with a the Flow direction of the cooling air flow determining channel longitudinal axis 7 'before, the is inclined so radially that the nozzle passage 71 passing Cooling air flow is directed radially outward.
  • the radially outside lying passage opening 19 arranged in alignment with the nozzle channel 71, whereby a free and unhindered foreign particle propagation along the Mainstream can be done.
  • the channel longitudinal axis 7 'of the nozzle channel 71 closes with the axis of rotation of the wheel disc 3 an angle ⁇ , preferably between 40 ° and 50 °.
  • the annular chamber 18 is on the one hand by the turbine stator 1 and on the other bounded by the deflection unit 9, the one substantially radially oriented flow channel within the annular chamber 18 includes. outgoing from the nozzle channel 71, it is in particular due to the by the in Circumferential circumferential swirl flow caused centrifugal force for the Foreign particles not possible, along the annular chamber 18 deflected radially inward to become and to pass through the radially inner passage opening 20.
  • the exit contour of the passage opening 20 looks comparable to Passage opening 19 before a flow channel 21, whose Flow channel longitudinal axis by an angle ⁇ , preferably 0 ° ⁇ ⁇ 35 ° is inclined radially outward. This ensures that the clean cooling air in the direction of the cooling disc 6 located in the rotating wheel disc 6 opens.
  • FIG. 8 is a further schematic longitudinal sectional view the device already shown in Fig. 7b for the separation of foreign particles out.
  • Essential is the radially outwardly inclined channel longitudinal axis 7 'of Nozzle channels 71, which at the same time also obliquely to the tangential plane for impressing a in the circumferential direction within the annular space 8 propagating swirl flow is inclined.
  • the schematized channel feeder in the lower part of Fig. 8 shows a axial plan view of the nozzle channel 71, by an angle ⁇ to the axis of rotation is inclined. This results in a within the annular space 8 by two Flow direction components a and u compound swirl flow c.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04103026A 2003-07-05 2004-06-29 Dispositif de séparation de particules étrangères contenues dans des fluides de refroidissement d'aubes mobiles d'une turbine Withdrawn EP1503046A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10330471 2003-07-05
DE10330471A DE10330471A1 (de) 2003-07-05 2003-07-05 Vorrichtung zum Abscheiden von Fremdpartikeln aus der den Laufschaufeln einer Turbine zuführbaren Kühlluft

Publications (2)

Publication Number Publication Date
EP1503046A2 true EP1503046A2 (fr) 2005-02-02
EP1503046A3 EP1503046A3 (fr) 2012-07-04

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US (1) US7137777B2 (fr)
EP (1) EP1503046A3 (fr)
DE (1) DE10330471A1 (fr)

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EP2378066A3 (fr) * 2010-04-16 2011-12-28 MTU Aero Engines GmbH Rotor pour une turbomachine
EP2060741A3 (fr) * 2007-11-19 2013-03-06 Rolls-Royce plc Agencement de turbine
US8851847B2 (en) 2010-11-15 2014-10-07 Mtu Aero Engines Gmbh Rotor for a turbo machine
EP3521571A1 (fr) * 2018-01-31 2019-08-07 United Technologies Corporation Refroidissement par impact de plate-forme des aubes de turbine

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US8578720B2 (en) * 2010-04-12 2013-11-12 Siemens Energy, Inc. Particle separator in a gas turbine engine
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US8584469B2 (en) * 2010-04-12 2013-11-19 Siemens Energy, Inc. Cooling fluid pre-swirl assembly for a gas turbine engine
KR101232609B1 (ko) * 2010-12-21 2013-02-13 두산중공업 주식회사 가스터빈 엔진의 로터 블레이드 프리 스월 냉각 장치
US9080449B2 (en) * 2011-08-16 2015-07-14 United Technologies Corporation Gas turbine engine seal assembly having flow-through tube
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US9988936B2 (en) 2015-10-15 2018-06-05 General Electric Company Shroud assembly for a gas turbine engine
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US11511222B2 (en) 2019-08-15 2022-11-29 Pratt & Whitney Canada Corp. Anti-contamination baffle for cooling air systems
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CN112089276B (zh) * 2020-08-19 2022-03-01 河南工程学院 一种服装设计样品展示装置
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EP0690202A2 (fr) * 1994-06-30 1996-01-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Arrangement pour la séparation des particules de poussière de l'air de refroidissement des aubes de turbine
EP1174589A1 (fr) * 2000-06-30 2002-01-23 Alstom (Switzerland) Ltd Séparateur de poussière pour une turbine à gaz

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1741874A2 (fr) * 2005-07-01 2007-01-10 Rolls-Royce plc Agencement de montage pour aube de turbine
EP1741874A3 (fr) * 2005-07-01 2014-01-22 Rolls-Royce plc Agencement de montage pour aube de turbine
EP2060741A3 (fr) * 2007-11-19 2013-03-06 Rolls-Royce plc Agencement de turbine
EP2378066A3 (fr) * 2010-04-16 2011-12-28 MTU Aero Engines GmbH Rotor pour une turbomachine
US8851847B2 (en) 2010-11-15 2014-10-07 Mtu Aero Engines Gmbh Rotor for a turbo machine
EP3521571A1 (fr) * 2018-01-31 2019-08-07 United Technologies Corporation Refroidissement par impact de plate-forme des aubes de turbine
US10526917B2 (en) 2018-01-31 2020-01-07 United Technologies Corporation Platform lip impingement features

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Publication number Publication date
EP1503046A3 (fr) 2012-07-04
US20050002778A1 (en) 2005-01-06
US7137777B2 (en) 2006-11-21
DE10330471A1 (de) 2005-02-03

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