WO2019022862A1 - Agencement de déviation de particules pour réduire l'ingestion de particules dans un moteur à turbine à combustion - Google Patents

Agencement de déviation de particules pour réduire l'ingestion de particules dans un moteur à turbine à combustion Download PDF

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Publication number
WO2019022862A1
WO2019022862A1 PCT/US2018/038149 US2018038149W WO2019022862A1 WO 2019022862 A1 WO2019022862 A1 WO 2019022862A1 US 2018038149 W US2018038149 W US 2018038149W WO 2019022862 A1 WO2019022862 A1 WO 2019022862A1
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WO
WIPO (PCT)
Prior art keywords
particulate
deflecting arrangement
deflecting
arrangement
flow
Prior art date
Application number
PCT/US2018/038149
Other languages
English (en)
Inventor
Reinhard Schilp
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
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 Aktiengesellschaft, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Publication of WO2019022862A1 publication Critical patent/WO2019022862A1/fr

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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

  • Disclosed embodiments are generally related to a combustion turbine engine, and, more particularly, to a particulate-deflecting arrangement for reducing ingestion of particulates into a turbine section of a combustion turbine engine.
  • a combustion turbine engine such as a gas turbine engine, includes for example a compressor section, a combustor section and a turbine section. Intake air is compressed in the compressor section and then mixed with fuel. The mixture is ignited in the combustor section to produce a high-temperature and high-pressure flow of combustion gases conveyed by a transition duct system to the turbine section of the engine, where thermal energy is converted to mechanical energy.
  • Particulates either picked-up from the ambient environment or from within the engine, may reach the mid-frame of the combustion turbine engine through a flow of cooling fluid (e.g., air) conveyed from the compressor section to the turbine section, such as may be conveyed into a first stage turbine vane structure. If left unimpeded, these particulates could eventually clog cooling features and channels in components in the turbine section, such as vanes and blades. To reduce ingestion of such particulates into the turbine section of the gas turbine engine, various schemes have been employed in the past. See US patent 4,820,123 for general background information in connection with certain known schemes.
  • cooling fluid e.g., air
  • FIG. 1 is a fragmentary, generally frontal, isometric view of a disclosed particulate-deflecting arrangement for reducing ingestion of particulates into a turbine section of a combustion turbine engine.
  • FIG. 2 is a fragmentary, generally lateral isometric view of a disclosed particulate-deflecting arrangement.
  • FIG. 3 is a fragmentary, isometric view of one non-limiting embodiment of tubular members that may be arranged through apertures circumferentially arranged in a deflector member of a disclosed particulate-deflecting arrangement.
  • the inventor of the present invention has recognized certain issues that can arise in connection with certain known arrangements for reducing ingestion of particulates into the turbine section of a combustion turbine engine.
  • arrangements may include a ramp mounted upstream of the first stage turbine vane structure with respect to a flow of cooling air conveyed into the first stage turbine vane structure.
  • the ramp redirects the flow of cooling air and is somewhat effective to prevent relatively large particulates from making the relatively sharp turn involved for the flow of cooling air to get into the turbine section, such as through a gap between a transition exit and the first stage turbine vane structure.
  • This gap must be sufficiently large to avoid introducing incremental pressure drop to the flow of cooling air being conveyed into the stage one turbine vane structure.
  • the presence of such a large gap makes feasible for medium-size particles, for example, to be ingested into the turbine section with the potential for clogging the cooling features and channels in the components in the turbine section.
  • the present inventor proposes an innovative particulate-deflecting arrangement that advantageously reduces the gap (e.g., spacing) between the transition exit and the first stage turbine vane structure. Accordingly, in a cost-effective and reliable manner, the proposed particulate-deflecting arrangement is expected to reduce ingestion of particulates into the turbine section of the combustion turbine engine, without compromising a desired pressurization level for the flow of cooling air being conveyed to the turbine section. [0014] In the following detailed description, various specific details are set forth in order to provide a thorough understanding of such embodiments.
  • FIG. 1 is a fragmentary, generally frontal, isometric view of a disclosed parti culate-deflecting arrangement 10 for reducing ingestion of particulates into a turbine section of a combustion turbine engine.
  • a deflector member 12 is annularly arranged between a casing 14 of the combustion turbine engine and a transition duct exit 16 (for simplicity of illustration just an arc segment of parti culate-deflecting arrangement 10 is shown in the figures).
  • a plurality of conduits 18, such as a plurality of tubular members, is arranged in deflector member 12 to convey a flow of cooling fluid received from the compressor stage into the turbine section.
  • Each conduit 18 includes a respective inlet 20 configured to protrude (conceptually analogous to an uprightly positioned collar) relative to a flow-deflecting surface 22 of deflector member 12.
  • Inlet 20 is angled relative to a main direction of the flow of cooling fluid (without limitation, conceptually represented by arrow 19 in FIG. 1).
  • This protruding arrangement of inlet 20 in lieu of an inlet configured to be flush with flow-deflecting surface 22 substantially reduces the likelihood of ingestion of particulates that may be contained in the flow of cooling fluid received from the compressor stage. For example, such particulates would strike the protruding side wall of inlet 20, and thus would be separated from the flow of cooling fluid being redirected by deflector member 12.
  • This redirected flow of cooling fluid (without limitation, conceptually represented by arrow 23 in FIG. 1), which would be substantially free of particulates ⁇ such as large or mid-size particulates, relative to the size of the cooling features or channels that otherwise could be clogged in components in the turbine section, such as vanes and blades ⁇ essentially would be the flow of cooling fluid conveyed into the turbine section through conduits 18. It should be appreciated that aspects of disclosed embodiments are not limited to the specific geometrical arrangements (e.g., inclination of deflector member 12, tilt angle of inlet 20 relative to flow-deflecting surface 22) and flow directions illustrated in the figures.
  • protruding inlet 20 is shown as being generally perpendicular to flow-deflecting surface 22, it will be appreciated that this aspect should be construed as a non-limiting illustration since the specific angular relationship between protruding inlet 20 and flow-deflecting surface 22 need not be perpendicular and may be readily tailored based on the needs of a given application, so long as the inlet is appropriately angled (e.g., tilted) relative to the main direction of the flow of cooling fluid.
  • conduits 18, may comprise a plurality of unrestricted conduits, e.g., tubular members, round tubes or any desired shape, as may be received in apertures 24 (one such aperture is shown without a tube in FIG. 3) circumferentially arranged in deflector member 12.
  • apertures 24 one such aperture is shown without a tube in FIG. 3
  • at least some of the plurality of round tubes may be mounted or otherwise affixed to deflector member 12 so that a respective axially-intermediate tube location 26 between mutually opposed first and second ends 28, 30 of the tube is centrally located in a respective aperture.
  • inlet 20 may extend between first end 28 of the tube and the respective axially-intermediate tube location 26, and a respective outlet 32 would extend between the respective axially-intermediate tube location 26 and the second end 30 of the tube.
  • Outlet 32 may be configured to protrude away from a surface 34 opposite flow-deflecting surface of deflector member 12.
  • the number of conduits 18 e.g., number of round tubes
  • the respective diameter of such tubes may be chosen so that the level of pressure drop in the flow of cooling fluid conveyed into the turbine section is within a desired level. For example, below the level of pressure drop that would develop in the flow of cooling fluid using other filtering techniques, e.g., using restriction filters in lieu of unrestricted conduits 18.
  • deflector member 12 may be disposed between a first flange 36 and a second flange 38 of particulate-deflecting arrangement 10.
  • first flange 36 may be configured for affixing particulate-deflecting arrangement 10 to a corresponding surface of casing 14.
  • second flange 38 may be configured for establishing a gap 40 (FIG. 2) between transition duct exit 16 and particulate- deflecting arrangement 10. This gap may provide sufficient clearance to
  • transition duct exit 16 accommodates displacements that may occur between transition duct exit 16 and particulate-deflecting arrangement 10 during operation of the engine.
  • a shielding member 42 may extend radially inward from deflector member 12 toward casing 14.
  • Shielding member 42 may be arranged upstream of outlet 32 for shielding entry of particulates through orifices 44 (e.g., pre-swirler supply orifices) constructed in casing 14, and which are in fluid communication with the turbine section. It will be further appreciated that shielding member 42 constitutes a support structure (e.g., a support leg) that contributes to the structural integrity of parti culate-deflecting arrangement 10. In one non-limiting embodiment, shielding member 42 is spaced apart from a circumferential periphery of orifice 44, and shielding member 42 may be shaped to define an arc positioned to span a corresponding arc of the circumferential periphery of orifice 44.
  • orifices 44 e.g., pre-swirler supply orifices
  • disclosed embodiments are expected to provide in a cost- effective manner a particulate-deflecting arrangement effective for reducing ingestion of particulates into the turbine section of the combustion turbine engine, without compromising a desired pressurization level for the flow of cooling air being conveyed to the turbine section.
  • Disclosed embodiments are expected to lower a likelihood of overheating due to clogging of cooling features and channels in components in the turbine section, such as vanes and blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un agencement de déviation de particules (10) pour réduire l'ingestion de particules dans une section de turbine d'un moteur à turbine à combustion. Cet agencement comprend un élément déflecteur (12) disposé de manière annulaire entre un boîtier du moteur à turbine à combustion et une sortie de conduit de transition. Des conduits, par exemple des conduits sans restriction, sont agencés dans l'élément déflecteur pour transporter un flux de fluide de refroidissement reçu d'un étage de compresseur dans la section de turbine. Chaque conduit (18) définit une entrée respective (20) configurée pour faire saillie (non affleurant) par rapport à une surface de déviation d'écoulement (22) de l'élément déflecteur (12). L'entrée respective est dans un angle (par exemple, inclinée) par rapport à une direction principale du flux de fluide de refroidissement. Cet agencement est efficace pour réduire l'ingestion de particules dans la section de turbine du moteur de turbine à combustion, sans compromettre le niveau de pressurisation souhaité pour le flux d'air de refroidissement transporté vers la section de turbine.
PCT/US2018/038149 2017-07-24 2018-06-19 Agencement de déviation de particules pour réduire l'ingestion de particules dans un moteur à turbine à combustion WO2019022862A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201762536231P 2017-07-24 2017-07-24
US62/536,231 2017-07-24

Publications (1)

Publication Number Publication Date
WO2019022862A1 true WO2019022862A1 (fr) 2019-01-31

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4466239A (en) * 1983-02-22 1984-08-21 General Electric Company Gas turbine engine with improved air cooling circuit
US4820123A (en) 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US20050229606A1 (en) * 2004-04-15 2005-10-20 Snecma Moteurs Annular combustion chamber for a turbomachine with an improved inner fastening flange
US20090255230A1 (en) * 2006-08-22 2009-10-15 Renishaw Plc Gas turbine
WO2014149353A1 (fr) * 2013-03-15 2014-09-25 General Electric Company Accélérateur cyclonique de séparation d'impuretés pour turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4466239A (en) * 1983-02-22 1984-08-21 General Electric Company Gas turbine engine with improved air cooling circuit
US4820123A (en) 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US20050229606A1 (en) * 2004-04-15 2005-10-20 Snecma Moteurs Annular combustion chamber for a turbomachine with an improved inner fastening flange
US20090255230A1 (en) * 2006-08-22 2009-10-15 Renishaw Plc Gas turbine
WO2014149353A1 (fr) * 2013-03-15 2014-09-25 General Electric Company Accélérateur cyclonique de séparation d'impuretés pour turbine

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