EP1574667B1 - Diffuseur pour compresseur - Google Patents

Diffuseur pour compresseur Download PDF

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Publication number
EP1574667B1
EP1574667B1 EP20040004895 EP04004895A EP1574667B1 EP 1574667 B1 EP1574667 B1 EP 1574667B1 EP 20040004895 EP20040004895 EP 20040004895 EP 04004895 A EP04004895 A EP 04004895A EP 1574667 B1 EP1574667 B1 EP 1574667B1
Authority
EP
European Patent Office
Prior art keywords
constriction
diffuser
gas turbine
wall
compressor
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.)
Expired - Lifetime
Application number
EP20040004895
Other languages
German (de)
English (en)
Other versions
EP1574667A1 (fr
Inventor
Christian Dr. Cornelius
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
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP20040004895 priority Critical patent/EP1574667B1/fr
Publication of EP1574667A1 publication Critical patent/EP1574667A1/fr
Application granted granted Critical
Publication of EP1574667B1 publication Critical patent/EP1574667B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps

Definitions

  • the invention relates to a gas turbine with a compressor diffuser and there a measure for optimizing a radial mass flow distribution at the inlet of the compressor diffuser.
  • the invention also relates to a diffuser itself.
  • a diffuser is known in its most general form, a component of a pipeline in which the cross-section grows gradually. This increase in cross-section causes a decrease in the velocity of the medium flowing through it, while the static pressure increases simultaneously.
  • a diffuser is usually arranged at the outlet of the gas turbine, in particular immediately after the turbine, and / or at the outlet of the compressor.
  • the invention is concerned with the mass flow or total pressure distribution required for optimum operation of the diffuser.
  • the compressor outlet diffuser shown there is designed as an axial diffuser and thus comprises an annular channel.
  • the inner, hub-side contour of the annular channel is cylindrical and the outer wall is conical, so that the cross-sectional enlargement of the diffuser along its axial extent is formed mainly by the increase of the radius of the outer wall.
  • Immediately upstream of the diffuser freestanding vanes are placed as a Nachleitrad, the free ends of the inner wall of the diffuser are facing gap formation.
  • a use of freestanding guide vanes leads, in particular in the case of larger radial gaps, to a considerable drop in the velocity of the flowing working medium, that is to say of the heated gas, in the hub region of a turbine shaft at the outlet of a secondary guide wheel.
  • the speed drop is accompanied by a total pressure drop.
  • the velocity and pressure distribution is especially unfavorable when a cross-sectional widening takes place within the diffuser exclusively via a reduction of the hub radius of the hub-side inner contour of the diffuser.
  • a weakened velocity profile in the region of the hub-side inner contour then leads to lossy flow separations on the inner contour of the diffuser. This significantly limits the pressure recovery of the diffuser and thus its overall efficiency.
  • a turbine outlet diffuser with a provided on its outer wall constriction known.
  • the constriction of the diffuser channel is located immediately downstream of the trailing edge of the last turbine stage blade, on the diffuser outer wall.
  • the EP 1 227 217 treats such a constriction downstream of the last blade of the turbine.
  • the invention is therefore based on the object of specifying a gas turbine optimized with a view to avoiding or reducing the abovementioned disadvantages with a diffuser.
  • the advantage of the invention is that a modification of the mass flow in the direction of the hub of the turbine rotor is caused by the modification of the inner contour of the diffuser housing just in a compressor diffuser through the constriction. In the area of the hub thus increases the speed level.
  • the speed drop caused by the hub-side radial gaps, that is to say by the distance between the upstream of the diffuser and the stationary rotor vanes and the hub of the turbine rotor, is thus largely compensated.
  • the constriction is located on the inside of the outer wall of the diffuser housing.
  • the constriction can be caused by material being deposited on the inside of the outer wall of the diffuser housing. Another possibility of forming such a constriction is that an adapted, the constriction-containing shaping of the outer wall of the diffuser housing is selected.
  • the constriction in the interior of the diffuser gradually decreases in the direction of flow of the medium flowing through, so that the constriction does not influence the intended mode of operation of the diffuser (speed reduction and pressure increase for the medium flowing through) negligibly or negligibly.
  • the constriction at the inlet of the diffuser is not abrupt but continuous and in a manner in which in the direction of the medium flowing through an increase of the constriction up to a maximum constriction is such that the increase in constriction to the maximum constriction significantly larger is as the decrease in the constriction following the maximum constriction.
  • a gas turbine has a compressor for combustion air, a combustion chamber and a turbine for driving both the compressor and a working machine, for.
  • a generator on.
  • the turbine and the compressor are arranged on a common, also referred to as a turbine rotor turbine shaft, with which the machine is connected, and which is rotatably mounted about its longitudinal axis.
  • the combustion chamber is equipped with at least one burner for the combustion of a liquid or gaseous fuel.
  • the compressor as well as the turbine each have a number of rotatable blades connected to the turbine shaft.
  • the blades are arranged in a ring on the turbine shaft and thus form a number of blade rows.
  • both the compressor and the turbine include a number of stationary vanes which are also annularly mounted to form vanes rows on an inner wall of the housing of the compressor or turbine.
  • the blades serve to drive the turbine shaft by momentum transfer from the turbine flowing through the working fluid.
  • the guide vanes serve to guide the flow of the working medium between two respective rows of blades or rotor blade rings viewed in the flow direction of the working medium.
  • a successive pair of a ring of vanes or a row of vanes and a ring of blades or a blade row is also referred to as a turbine stage or as a compressor stage.
  • the compressor or turbine housing Between the blades and the inner contour of the respective surrounding housing, so the compressor or turbine housing remains a radial gap whose size is dimensioned so that during operation of the gas turbine even with thermal expansion of the respective materials stripping of the blades is excluded at the respective inner housing.
  • a radial gap remains between the stationary vanes and the turbine shaft. This is also such that a contact between the vanes and the turbine shaft is excluded.
  • FIG. 1 shows a sectional view of a gas turbine with a arranged at the output of its compressor diffuser 1 with a diffuser housing 2.
  • the diffuser housing 2 has in a connection region 3, ie in the region of the transition from the compressor of the gas turbine to the diffuser 1, a constriction 5 reducing the inner radius of the housing 2 on.
  • a portion of the diffuser 1 belonging to the connection region 3 is referred to as the inlet 4 of the diffuser 1.
  • the inlet 4 has an annular space contour. The dimensions of the inlet 4 are determined essentially by its inner radius.
  • the flow space of the diffuser 1 is bounded radially on the outside by an outer wall of the diffuser housing 2 and radially inward by a hub-side inner contour.
  • the constriction 5 decreases gradually within the diffuser 1 in the flow direction of the medium flowing through, ie the compressed air.
  • the flow direction runs from left to right.
  • At the inlet 4 of the diffuser 1 takes place - also in the direction of the medium flowing through - an increase in the constriction to a maximum constriction 5 such that the increase in constriction to the maximum constriction 5 is significantly greater than the decrease in constriction following the maximum Constriction 5.
  • the quantification of an aspect ratio between a distance during which the constriction at the inlet 4 initially increases to the maximum constriction 5 and a distance during which the constriction within the diffuser 1 then decreases again is possible as follows:
  • the length of a distance along the Outer contour of the diffuser housing 2 parallel to the flow direction of the medium, during which the constriction increases to the maximum constriction 5, is less than one fifth of the length of a distance during which the constriction decreases from the maximum constriction 5 again.
  • the one-sided on the inside of the diffuser housing 2, in particular in the region of the Diffusoreinlasses 4, made radius reduction (constriction 5) causes a redistribution of the mass flow in the direction of the hub of the turbine rotor. This increases the speed level in the hub area (see also FIG. 2 ). Overall, there is a substantially improved velocity and total pressure distribution at the inlet 4 of the diffuser 1. Increasing the near-net velocity level causes the hub boundary layer to run at a substantially higher pressure, thus improving the pressure recovery and overall compressor efficiency.
  • FIG. 2 shows a graphical representation of a theoretically calculated speed increase in the region of the hub of a turbine runner.
  • the abscissa shows the increase in the axial velocity compared to the unmodified design.
  • r * as the radius, the distance from the hub of the turbine rotor is removed. It can be seen the significant increase in speed in the immediate hub area, ie in the area in which so far due to a caused by the radial gap at the outer end of the vanes slit flow a drop in speed was observed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (6)

  1. Turbine à gaz comprenant un diffuseur ( 1 ) disposé à la sortie de son compresseur et ayant un carter ( 2 ) de diffuseur,
    dans laquelle le carter ( 2 ) du diffuseur délimite un contour ( 6 ) d'espace annulaire par une paroi extérieure à l' extérieur radialement et par un contour intérieur à l' intérieur radialement et a une zone ( 3 ) de raccord dans la zone de la transition du compresseur au diffuseur, ( 1 ) comprenant immédiatement en amont du diffuseur ( 1 ) des aubes ( 8 ) directrices qui sont disposées suivant une couronne et dont les extrémités libres respectives dépassent respectivement du contour intérieur en formant une fente radiale,
    caractérisée en ce que
    dans la zone ( 3 ) de raccord il est prévu un rétrécissement ( 5 ) faisant le tour et se trouvant à l'intérieur de la paroi extérieure pour provoquer une re-répartition du courant massique en direction du contour intérieur et compenser ainsi en grande partie l'effondrement de vitesse provoqué par les fentes radiales dans la zone du contour intérieur.
  2. Turbine à gaz suivant la revendication 1,
    dans laquelle le resserrement ( 5 ) est provoqué par une accumulation de matière sur la face intérieure de la paroi extérieure
  3. Turbine à gaz suivant la revendication 1 ou 2,
    dans lequel le resserrement (5) est provoqué par un façonnage adapté de la paroi extérieure.
  4. Turbine à gaz suivant les revendications précédentes,
    dans lequel le resserrement ( 5 ) diminue peu à peu dans le sens d' écoulement du fluide qui passe.
  5. Turbine à gaz suivant la revendication 4,
    dans lequel il s' effectue à l'entrée ( 4 ) du diffuseur ( 1 ) dans la direction du fluide qui passe, une augmentation du resserrement jusqu' à un resserrement ( 5 ) maximum de sorte que l'augmentation du resserrement jusqu' au resserrement ( 5 ) maximum est nettement plus grand que la diminution du resserrement dans le raccord au resserrement ( 5 ) maximum.
  6. Turbine à gaz suivant la revendication 5,
    dans laquelle la longueur d' une étendue le long du contour extérieur du carter ( 2 ) du diffuseur parallèlement à la direction d'écoulement du fluide pendant laquelle le resserrement augmente jusqu' au resserrement ( 5 ) maximum est plus petit qu' un cinquième de la longueur d' une étendue pendant laquelle le resserrement diminue à nouveau à partir du resserrement ( 5 ) maximum.
EP20040004895 2004-03-02 2004-03-02 Diffuseur pour compresseur Expired - Lifetime EP1574667B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20040004895 EP1574667B1 (fr) 2004-03-02 2004-03-02 Diffuseur pour compresseur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20040004895 EP1574667B1 (fr) 2004-03-02 2004-03-02 Diffuseur pour compresseur

Publications (2)

Publication Number Publication Date
EP1574667A1 EP1574667A1 (fr) 2005-09-14
EP1574667B1 true EP1574667B1 (fr) 2013-07-17

Family

ID=34814245

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EP20040004895 Expired - Lifetime EP1574667B1 (fr) 2004-03-02 2004-03-02 Diffuseur pour compresseur

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EP (1) EP1574667B1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2194231A1 (fr) 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Diffuseur annulaire pour une turbomachine axiale
DE102012215412A1 (de) 2012-08-30 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine und Verfahren zur Herstellung einer solchen Baugruppe
CN115962154A (zh) * 2023-03-17 2023-04-14 潍柴动力股份有限公司 过渡段子午流道在机匣侧变窄的压气机、发动机和汽车

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1448244A (fr) * 1965-06-23 1966-08-05 Procédé et dispositif pour l'exploitation d'une installation de turbine à vapeur
US3625630A (en) * 1970-03-27 1971-12-07 Caterpillar Tractor Co Axial flow diffuser
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
US4180972A (en) * 1978-06-08 1980-01-01 General Motors Corporation Combustor support structure
JPS5520607U (fr) * 1978-07-26 1980-02-08
GB2057672B (en) * 1979-07-04 1983-05-18 Rolls Royce Gas turbine combustion chamber
SU1657672A1 (ru) * 1986-07-28 1991-06-23 Производственное объединение "Невский завод" им.В.И.Ленина Диффузор турбомашины
DE19803161C2 (de) * 1998-01-28 2000-03-16 Alstom Energy Syst Gmbh Gasturbinenschalldämpfer mit Diffusor
JP4107765B2 (ja) * 1999-06-15 2008-06-25 三菱重工業株式会社 ガスタービン圧縮機吐出空気の抽気方法
US6442939B1 (en) * 2000-12-22 2002-09-03 Pratt & Whitney Canada Corp. Diffusion mixer
JP3912989B2 (ja) * 2001-01-25 2007-05-09 三菱重工業株式会社 ガスタービン
JP3564420B2 (ja) * 2001-04-27 2004-09-08 三菱重工業株式会社 ガスタービン

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Publication number Publication date
EP1574667A1 (fr) 2005-09-14

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