EP2083148A2 - Turbine à gaz dotée d'un compresseur muni d'un revêtement de rodage et procédé de rodage des extrémités libres des aubes d'un compresseur de turbine à gaz - Google Patents

Turbine à gaz dotée d'un compresseur muni d'un revêtement de rodage et procédé de rodage des extrémités libres des aubes d'un compresseur de turbine à gaz Download PDF

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Publication number
EP2083148A2
EP2083148A2 EP09000952A EP09000952A EP2083148A2 EP 2083148 A2 EP2083148 A2 EP 2083148A2 EP 09000952 A EP09000952 A EP 09000952A EP 09000952 A EP09000952 A EP 09000952A EP 2083148 A2 EP2083148 A2 EP 2083148A2
Authority
EP
European Patent Office
Prior art keywords
inlet layer
blades
gas turbine
layer
liquid
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Withdrawn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
EP09000952A
Other languages
German (de)
English (en)
Other versions
EP2083148A3 (fr
Inventor
Ingo Jahns
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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
Priority claimed from DE200810005480 external-priority patent/DE102008005480A1/de
Priority claimed from DE102008005482A external-priority patent/DE102008005482A1/de
Priority claimed from DE102008005479A external-priority patent/DE102008005479A1/de
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2083148A2 publication Critical patent/EP2083148A2/fr
Publication of EP2083148A3 publication Critical patent/EP2083148A3/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F04D27/0238—Details or means for fluid reinjection
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/222—Silicon
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics

Definitions

  • the invention relates to a gas turbine according to the features of the preambles of the independent claims.
  • the invention relates to a gas turbine having a compressor comprising at least one row of blades, the blades each being provided with a free end adjacent the free end of the blade at an annular housing portion and / or at an annular portion Drum area is formed an inlet layer.
  • Today's axial compressors consist of a rotor with at least one blade row and a housing. This blade row should have the smallest possible distance to the housing in order to avoid efficiency losses.
  • inlet linings are introduced in the housing. In the case of brushing areas of the inlet lining are removed.
  • the gap is adjusted so that the rotor blades run into this run-in layer only slightly or not at all. This ensures that a small gap exists under normal conditions. Under extreme operating conditions, the rotor blade can run into these run-in layers stronger and remove material there.
  • the invention has for its object to provide a gas turbine and a method for running in blades, which avoid the disadvantages of the prior art with a simple structure and simple, reliable operation and has a high degree of reliability.
  • a liquid is thus used according to the invention for sealing, wherein the thickness of the layer is preferably only in the tenth of a millimeter range.
  • materials are used which are readily available, e.g. Water produced by combustion or oil necessary for lubrication.
  • the core of the invention according to the first aspect is therefore to form the inlet layer itself liquid permeable and thus to form on the surface of a liquid film which acts against the free blade ends and the Run-in behavior of the blades optimized. Direct contact with the inlet layer is thus avoided under certain operating conditions, since the free blade ends abut against the liquid film.
  • the invention provides that the inlet layer is porous and can be acted upon with an air-hardening material.
  • the air-hardenable or air-hardening material is stored in an annular storage chamber or in an annular storage container. Upon contact of the surface of the annular housing portion or drum portion with the free blade ends of the compressor blades, the air-hardening material is released and passed through the inlet layer. Through this it penetrates into the air flow of the annular channel of the rotor (compressor) and hardens.
  • a method according to the second aspect of the invention can be considered as a method for entering free end portions of blades of a compressor of a gas turbine, wherein the end portions are brought into contact with at least one substantially annular inlet layer of an annular housing portion, and wherein a surface of the inlet layer with describe an air-curable material can be acted upon describe. It is advantageously provided that silicone is used as the air-curable material, and / or another curable material is used.
  • the invention provides that the inlet layer is porous and can be acted upon with a liquid.
  • a self-healing layer is formed on the surface of the inlet layer by evaporation of the liquid.
  • the gap between rotor blades and inlet layer is set according to the invention so that under normal operating conditions, the top layer is not damaged. If an extreme maneuver causes the rotor blades to run into the top layer, it is removed and the basic structure of the inlet layer is uncovered. Now the self-healing process starts. It is as long as liquid evaporates until a dissolved substance in the liquid settles on the damaged surface and closes the damaged cover layer again.
  • the Fig. 1 shows a schematic structure of a partial view of a compressor or compressor of a gas turbine to be used according to the invention.
  • a rotor 14 (rotor drum) is rotatably mounted in an annular housing portion 15, as shown in the prior art.
  • the rotor 14 comprises a drum region 13, on which rows of rotor blades 11 are mounted. Alternating rows of stator blades 18 are on the annular Housing area 15 stored.
  • a compressor 12 is formed, as is known from the prior art.
  • Free blade ends 16 of the rotor blades 11 and stator blades 18 lie with a small gap on the wall of a housing 9 or the rotor drum.
  • an inlet layer 6 is provided in order to adjust the distance of the free blade ends of the surface of the housing 9 and the drum portion 13 by shrinkage.
  • the Fig. 6 shows a schematic structure of a partial view of a compressor or compressor according to the invention to be used gas turbine according to the first embodiment.
  • a rotor rotor drum
  • the rotor comprises a drum region on which rows of rotor blades are mounted. Alternating rows of stator blades are mounted on the annular housing portion.
  • a compressor is formed, as is known from the prior art.
  • the liquid is introduced via at least one inlet tube 109 (FIG. Fig. 3 ) is supplied to the housing 108. Via a chamber 113, the liquid can distribute evenly.
  • An inlaid support 111 also serves to seal the chamber 113 from an annulus between adjacent rows of blades.
  • run-in layer carrier 111 the inlet layer 106 is applied. Through holes 112 in the inlet layer carrier 111, the liquid reaches the inlet layer 106.
  • the base layer of the inlet layer 106 preferably consists of a porous, hygroscopic base material or capillary tube, so that the liquid can escape at the surface.
  • the liquid In order for the liquid to adhere well to the surface 115, it should have properties that increase the surface area, eg, be rough or grainy (see Fig. 5 ).
  • the liquid wets the surface 115 and forms a thin layer against which the rotor blades 102 (FIG. Fig. 6 ) can run under extreme operating conditions.
  • the cover layer of the inlet lining is inventively from the Liquid formed. The air flow entrains molecules / atoms of the liquid. So there are losses. The tougher the liquid, the lower the losses will be. Due to the pressure in the annulus, it may be necessary for the liquid to be pressurized.
  • a suction device is preferably mounted thereon ( Fig. 4 ).
  • the excess liquid can pass through the holes 112 in the inlet layer carrier 111 into a chamber 117.
  • This chamber 117 is formed in the example shown by the inlet layer carrier 111 and an applied cover plate 116. From there, the liquid is removed via a suction pipe 114 from the compressor.
  • an advantageous embodiment of the invention provides that an electrically conductive liquid (for example atoms / molecules of the liquid are electrically conductive or by the addition of electrically conductive substances in an otherwise non-conductive liquid) is used.
  • an electrically conductive layer is additionally introduced, or the inlet layer 106 itself consists of an electrically conductive material.
  • This electrically conductive material is coated with an insulating layer to avoid direct contact with the electrically conductive liquid.
  • a voltage is now applied to the electrically conductive layer. The particles of the liquid are attracted by the tension and adhere better to the surface.
  • the splitting behavior of an engine is difficult to control.
  • the invention allows the rotor blades to enter the liquid under extreme conditions. Since the liquid can be constantly replaced, in contrast to a fixed inlet lining, a uniform and optimized gap can be set.
  • an air-curing (air-curable) material 201 eg silicone
  • This is stored in a storage container 202 behind the inlet layer carrier.
  • the wall of the storage container 202 is flexible, it consists for example of a plastic film 203th
  • an inlet layer 206 is applied on an inlet layer carrier 204. Holes / recesses 207 in the inlet layer carrier 204 allow the air-hardenable material (curing mass) to reach the inlet layer 206.
  • the base layer of the inlet layer 206 consists of a porous base material or has fine tubes.
  • pressurized air can be passed through the housing 209 into a chamber 210 and exert a pressure on the wall of the reservoir 202.
  • a gap between the rotor blades 11 (FIG. Fig. 1 ) and the inlet layer 206 is set in accordance with the invention such that under normal operating conditions the cover layer 208 (upper layer) is not damaged. If the rotor blades 11 enter the cover layer 208 during an extreme maneuver, this will be removed. As a result, the basic structure of the inlet layer 206 is exposed.
  • the air-hardening material (curing compound) is forced through the inlet layer 206 at the damaged location and comes into contact with the atmospheric oxygen of the compressor 12 and cures in the process.
  • the gas turbine according to the third embodiment will ideally use existing raw materials in operation.
  • water is used as the liquid. Combustion of the fuel releases carbon dioxide and water. The exhaust gases can the exhaust gas flow removed and the water are brought to condensation.
  • the substances used according to the invention can also be carried or recovered from the ambient air.
  • the carbon dioxide is dissolved in the water and it produces carbon dioxide.
  • According to the invention can thus be constructed a circuit with pump and cooling of the water.
  • the slightly carbonated water is passed over the lime, wherein the lime is converted to water-soluble calcium bicarbonate.
  • This calcium bicarbonate-containing water is now passed through a supply pipe 317 on the housing 309. Via a chamber 310, the liquid can be distributed evenly.
  • the inlet layer carrier 304 also serves at this point for sealing the chamber 310 with respect to the annular space 5 (FIG. Fig. 2 ).
  • the run-in layer 306 is applied in the run-in layer carrier 304. Through recesses 307 in the inlet layer carrier 304, the liquid reaches the inlet layer 306.
  • the base layer of the inlet layer 306 consists of a porous base material or tube, so that the calcium bicarbonate-containing water can penetrate them.
  • the uppermost layer 308 of the inlet layer 306 consists of a water-impermeable cover layer.
  • the gap between rotor blades 11 and inlet layer 306 is adjusted according to the invention so that the cover layer 308 is not damaged under normal operating conditions. If, during an extreme maneuver, the rotor blades 11 run into the cover layer 308, this is removed and the basic structure of the inlet layer 306 is uncovered. Now the self-healing process starts. It is as long as water evaporates until deposited on the damaged surface of a lime layer and the damaged cover layer 308 closes again.
  • the base layer of the inlet layer 306 consists of a porous base material or has fine tubes (capillary).
  • a suction device is preferably mounted thereon ( Fig. 9 ).
  • the excess liquid can pass through the holes 307 in the inlet layer carrier 304 into a chamber 301.
  • This chamber 301 is formed in the example shown by the inlet layer carrier 304 and an applied cover plate 302. From there, the liquid is removed via a suction pipe 303 from the compressor.
  • the splitting behavior of an engine is difficult to control.
  • the invention allows the run-in layer to regenerate itself and at least partially restore the run gap.

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  • 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)
EP09000952A 2008-01-23 2009-01-23 Turbine à gaz dotée d'un compresseur muni d'un revêtement de rodage et procédé de rodage des extrémités libres des aubes d'un compresseur de turbine à gaz Withdrawn EP2083148A3 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE200810005480 DE102008005480A1 (de) 2008-01-23 2008-01-23 Gasturbine mit einem Verdichter mit Einlaufschicht mit luftaushärtendem Material
DE102008005482A DE102008005482A1 (de) 2008-01-23 2008-01-23 Gasturbine mit einem Verdichter mit selbstheilender Einlaufschicht
DE102008005479A DE102008005479A1 (de) 2008-01-23 2008-01-23 Gasturbine mit einem Verdichter mit flüssigkeitsbeaufschlagter Einlaufschicht

Publications (2)

Publication Number Publication Date
EP2083148A2 true EP2083148A2 (fr) 2009-07-29
EP2083148A3 EP2083148A3 (fr) 2012-06-06

Family

ID=40469804

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09000952A Withdrawn EP2083148A3 (fr) 2008-01-23 2009-01-23 Turbine à gaz dotée d'un compresseur muni d'un revêtement de rodage et procédé de rodage des extrémités libres des aubes d'un compresseur de turbine à gaz

Country Status (2)

Country Link
US (1) US8257016B2 (fr)
EP (1) EP2083148A3 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9068507B2 (en) * 2011-11-16 2015-06-30 General Electric Company Compressor having purge circuit and method of purging
EP2886804B1 (fr) * 2013-12-20 2017-08-16 Safran Aero Boosters SA Dispositif d'étanchéité pour un compresseur de turbomachine
BE1024735B1 (fr) * 2016-11-15 2018-06-19 Safran Aero Boosters Sa Virole antigivre de compresseur de turbomachine axiale
CN108412761B (zh) * 2018-04-12 2024-03-01 河北昊方新能源科技有限公司 喷液冷却涡旋式空气压缩机

Citations (3)

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Publication number Priority date Publication date Assignee Title
WO2005028119A1 (fr) * 2003-09-25 2005-03-31 Gas Turbine Efficiency Ab Buse et procede destines au lavage de compresseurs de turbines a gaz
WO2005077554A1 (fr) * 2004-02-16 2005-08-25 Gas Turbine Efficiency Ab Procede et appareil permettant de nettoyer une turbine a gaz a turboreacteur a double flux
US7086233B2 (en) 2003-11-26 2006-08-08 Siemens Power Generation, Inc. Blade tip clearance control

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Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005028119A1 (fr) * 2003-09-25 2005-03-31 Gas Turbine Efficiency Ab Buse et procede destines au lavage de compresseurs de turbines a gaz
US7086233B2 (en) 2003-11-26 2006-08-08 Siemens Power Generation, Inc. Blade tip clearance control
WO2005077554A1 (fr) * 2004-02-16 2005-08-25 Gas Turbine Efficiency Ab Procede et appareil permettant de nettoyer une turbine a gaz a turboreacteur a double flux

Also Published As

Publication number Publication date
US8257016B2 (en) 2012-09-04
US20090196730A1 (en) 2009-08-06
EP2083148A3 (fr) 2012-06-06

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