EP3144540A1 - Étage de compresseur de turbine à gaz - Google Patents

Étage de compresseur de turbine à gaz Download PDF

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Publication number
EP3144540A1
EP3144540A1 EP15185447.8A EP15185447A EP3144540A1 EP 3144540 A1 EP3144540 A1 EP 3144540A1 EP 15185447 A EP15185447 A EP 15185447A EP 3144540 A1 EP3144540 A1 EP 3144540A1
Authority
EP
European Patent Office
Prior art keywords
compressor
gas turbine
aircraft engine
compressor stage
downstream
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.)
Granted
Application number
EP15185447.8A
Other languages
German (de)
English (en)
Other versions
EP3144540B1 (fr
Inventor
Werner Humhauser
Roland Matzgeller
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP15185447.8A priority Critical patent/EP3144540B1/fr
Priority to US15/245,388 priority patent/US10280934B2/en
Publication of EP3144540A1 publication Critical patent/EP3144540A1/fr
Application granted granted Critical
Publication of EP3144540B1 publication Critical patent/EP3144540B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/028—Layout of fluid flow through the stages
    • 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
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the present invention relates to a compressor stage for a gas turbine, a gas turbine having at least one such compressor stage, an aircraft engine with such a gas turbine and a method for designing such a compressor stage and a method for designing a compressor of such a gas turbine, in particular an aircraft engine.
  • compressor stages of gas turbines are designed so that their throttle number ⁇ is always smaller than 5.16 minus 1.33 times the aspect ratio AR ax defined by the quotient of average channel height h and average chord length l ax ( ⁇ ⁇ -1.33 ⁇ AR ax + 5,16).
  • An object of an embodiment of the present invention is to improve a gas turbine.
  • Claims 3, 5 and 8 provide a gas turbine with a compressor stage described herein, an aircraft engine with a gas turbine described herein or a method for designing a compressor of a gas turbine described here, in particular aircraft engine gas turbine, under protection.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • one or more compressor stages of a compressor or one or more compressor stages of a plurality of compressors of a gas turbine in particular an aircraft engine gas turbine, which (each) a playpens and a guide grid, aerodynamically designed so that the throttle factor ⁇ and the aspect ratio AR ax (respectively) of the condition defined by the quotient of mean channel height h and mean chord length l ax ⁇ > - 1 . 33 ⁇ AR ax + 5 . 16 enough.
  • one or more compressor stages for a compressor or one or more compressor stages for a plurality of compressors of a gas turbine in particular an aircraft engine gas turbine, in particular one or more compressor stages of a compressor or one or more compressor stages of a plurality of compressors of a gas turbine, in particular an aircraft engine gas turbine, each having a playpen and a guide grid, (respectively) of the condition ⁇ > - 1 . 33 ⁇ AR ax + 5 . 16 ⁇ with the throttle point and the h by the quotient of mean channel height and average chord length l ax defined aspect ratio AR ax.
  • a playpens in one embodiment comprises a plurality of circumferentially spaced blades disposed on a rotor which is rotatable (supported) about a main or machine axis, in particular by a turbine of the gas turbine.
  • the blades may be releasably or cohesively attached to the rotor or formed integrally therewith. In one embodiment, they can be uncovered or have a closed outer cover tape.
  • a guide grid in one embodiment has a plurality of circumferentially spaced vanes fixedly or adjustably disposed on a housing that engages around the rotor. In one embodiment, they can be uncovered or have a closed inner cover tape.
  • the baffle is disposed downstream of a downstream baffle or downstream of the playpens. It may in particular be a so-called Nachleitrad for the implementation of impressed by the rotating playpen kinetic in pressure energy of the gas turbine flowing air.
  • the compressor stage in the context of the present invention from the running and the guide grid.
  • the average chord length l ax is defined in the usual way as a geometric mean of the distance between the inlet and the outlet edge of the playpen or the compressor stage.
  • AR ax H / l ax ,
  • the aspect ratio AR ax is greater than 0.5. Additionally or alternatively, according to one embodiment, the aspect ratio AR ax is less than 2.5. In this way, a particularly advantageous compressor stage can be made available.
  • a total pressure ratio ⁇ of one or more of the compressors is at least 40, in particular at least 45. In this way, a particularly advantageous compressor can be made available.
  • a bypass ratio BPR (by-pass ratio) of the aircraft engine is at least 10, in particular at least 12. In this way, a particularly advantageous aircraft engine can be provided.
  • Fig. 1 shows in a partially schematic manner an aircraft engine with a fan 1 and a gas turbine, for illustrative purposes only and exemplarily only a compressor 9, a downstream combustion chamber 5, a high-pressure turbine 6, which is coupled to the compressor 9 via a rotor 10, and a Low-pressure turbine 7 which is coupled to the fan 1.
  • the gas turbine is flowed through by a core stream 8 and a secondary or sheath flow 2.
  • the compressor 9 has a plurality of compressor stages, each having a rotor-fixed playpens 3 and a downstream adjacent Leitgitter 4.
  • One or more of these compressor stages 3, 4 are or are designed such that the throttle digit ⁇ and the defined by the quotient of mean channel height h and average chord length l ax aspect ratio AR ax of the condition ⁇ > - 1 . 33 ⁇ AR ax + 5 . 16 is sufficient, the aspect ratio AR ax is greater than 0.5 and less than 2.5.
  • the total pressure ratio ⁇ of the compressor 9 is at least 45, the bypass ratio BPR of the aircraft engine at least 12th
  • the aircraft engine or the gas turbine in particular a low-pressure and a downstream high-pressure compressor, in a development also have a medium pressure compressor arranged therebetween, at least one of these compressors in the above exemplary with respect to the compressor 9 explained manner be or be can.
  • low and high pressure compressors may also be understood as a compressor in the sense of the present invention.
  • the fan 1 can be coupled in particular via a transmission to the high-pressure turbine 6.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
EP15185447.8A 2015-09-16 2015-09-16 Étage de compresseur de turbine à gaz Active EP3144540B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15185447.8A EP3144540B1 (fr) 2015-09-16 2015-09-16 Étage de compresseur de turbine à gaz
US15/245,388 US10280934B2 (en) 2015-09-16 2016-08-24 Gas turbine compressor stage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15185447.8A EP3144540B1 (fr) 2015-09-16 2015-09-16 Étage de compresseur de turbine à gaz

Publications (2)

Publication Number Publication Date
EP3144540A1 true EP3144540A1 (fr) 2017-03-22
EP3144540B1 EP3144540B1 (fr) 2023-05-10

Family

ID=54147096

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15185447.8A Active EP3144540B1 (fr) 2015-09-16 2015-09-16 Étage de compresseur de turbine à gaz

Country Status (2)

Country Link
US (1) US10280934B2 (fr)
EP (1) EP3144540B1 (fr)

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2406126A (en) * 1942-03-21 1946-08-20 Bbc Brown Boveri & Cie Blade arrangement for axial compressors
US2830754A (en) * 1947-12-26 1958-04-15 Edward A Stalker Compressors
US2749027A (en) * 1947-12-26 1956-06-05 Edward A Stalker Compressor
US2605956A (en) * 1949-08-13 1952-08-05 Chrysler Corp Power conversion machine
US2726806A (en) * 1950-12-02 1955-12-13 A V Roe Canada Ltd Axial compressor
US2846136A (en) * 1951-07-19 1958-08-05 Bbc Brown Boveri & Cie Multi-stage axial flow compressors
US2846137A (en) * 1955-06-03 1958-08-05 Gen Electric Construction for axial-flow turbomachinery
US2990106A (en) * 1956-10-12 1961-06-27 English Electric Co Ltd Axial flow multi-stage compressors
GB992941A (en) * 1963-11-29 1965-05-26 Bristol Siddeley Engines Ltd Improvements in rotary bladed compressors and turbines
US3775023A (en) * 1971-02-17 1973-11-27 Teledyne Ind Multistage axial flow compressor
US4116584A (en) * 1973-10-12 1978-09-26 Gutehoffnungshutte Sterkrade Ag Device for extending the working range of axial flow compressors
US4011028A (en) * 1975-10-16 1977-03-08 Anatoly Nikolaevich Borsuk Axial-flow transsonic compressor
DE102005052466A1 (de) * 2005-11-03 2007-05-10 Mtu Aero Engines Gmbh Mehrstufiger Verdichter für eine Gasturbine mit Abblasöffnungen und Einblasöffnungen zum Stabilisieren der Verdichterströmung
US8292574B2 (en) * 2006-11-30 2012-10-23 General Electric Company Advanced booster system
US7967571B2 (en) * 2006-11-30 2011-06-28 General Electric Company Advanced booster rotor blade
US20160052621A1 (en) * 2009-07-10 2016-02-25 Peter Ireland Energy efficiency improvements for turbomachinery
CH705822B1 (de) * 2011-11-16 2016-01-29 Alstom Technology Ltd Axialverdichter für eine Strömungsmaschine, insbesondere eine Gasturbine.
US9109608B2 (en) * 2011-12-15 2015-08-18 Siemens Energy, Inc. Compressor airfoil tip clearance optimization system
US10125724B2 (en) * 2012-01-17 2018-11-13 United Technologies Corporation Start system for gas turbine engines
US20130192198A1 (en) * 2012-01-31 2013-08-01 Lisa I. Brilliant Compressor flowpath
JP6185781B2 (ja) * 2013-07-23 2017-08-23 三菱日立パワーシステムズ株式会社 軸流圧縮機
US9759230B2 (en) * 2014-01-24 2017-09-12 Pratt & Whitney Canada Corp. Multistage axial flow compressor
US10378554B2 (en) * 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
H. GRIEB: "Projektierung von Turboflugtriebwerken", 22 November 2012, BIRKHÄUSER, ISBN: 3034896271, XP002755942 *
H. GRIEB: "Verdichter für Turbo-Flugtriebwerke", SPRINGER-VERLAG

Also Published As

Publication number Publication date
US10280934B2 (en) 2019-05-07
US20170074271A1 (en) 2017-03-16
EP3144540B1 (fr) 2023-05-10

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