EP2292934A2 - Compresseur axial doté d'un générateur d'impulsions d'écoulement - Google Patents

Compresseur axial doté d'un générateur d'impulsions d'écoulement Download PDF

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Publication number
EP2292934A2
EP2292934A2 EP10007218A EP10007218A EP2292934A2 EP 2292934 A2 EP2292934 A2 EP 2292934A2 EP 10007218 A EP10007218 A EP 10007218A EP 10007218 A EP10007218 A EP 10007218A EP 2292934 A2 EP2292934 A2 EP 2292934A2
Authority
EP
European Patent Office
Prior art keywords
rotor
flow
wall
axial compressor
compressor according
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Withdrawn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
EP10007218A
Other languages
German (de)
English (en)
Other versions
EP2292934A3 (fr
Inventor
Carsten Clemen
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
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2292934A2 publication Critical patent/EP2292934A2/fr
Publication of EP2292934A3 publication Critical patent/EP2292934A3/fr
Withdrawn legal-status Critical Current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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps

Definitions

  • the invention relates to an axial compressor which comprises within a compressor housing at least one rotor made of rotor blades connected to a drive shaft and a stator held on the housing inner wall and a flow pulse generator associated with the rotor gap present between the blade tips and the housing inner wall for stabilizing the rotor gap flow.
  • compressed fluid is taken from the rear stages of the compressor and re-blown in the blade tip region of the front rotors in order to increase the flow pulse at the gap and thus actively influence the rotor gap flow and to stabilize the gap vortex.
  • this mode of operation is disadvantageous in that the fluid in the compressor is more heated by the reintroduction of hot fluid from the rear of the compressor and thus the compressor efficiency drops.
  • the compressor stability can also be influenced passively by formations formed in the compressor housing over the blade tips.
  • a flow circulation caused by the injection conveys a certain amount of energy into the front region of the rotor tip, so that the momentum of the rotor inflow is increased and thus the rotor gap flow and finally the compressor operation are stabilized.
  • this housing design is difficult to manufacture and can also be damaged when entering the rotor.
  • the invention is therefore the object of developing an axial compressor of the type mentioned with respect to the flow pulse generator so that at a reduced manufacturing cost and without wear, a high local flow pulse for stabilizing the rotor gap flow and the compressor operation is achieved.
  • the basic idea of the invention consists in the arrangement of a flow pulse generator on the inner wall of the compressor housing, consisting of upstream of the rotor in the flow direction extending and tapering pulse channels for accelerating the near-wall flow.
  • the shape and dimension of the impulse channels directed towards the rotor gap is defined by circumferentially spaced-apart, gap-free fixed to the housing inner wall Separators determined.
  • the thus formed flow pulse generator is easy to manufacture and ensures a favorable flow of the rotor gap and effective stabilization of the rotor gap flow.
  • the operating range of the compressor is extended without adversely affecting the compressor efficiency.
  • the pulse channels are each bounded by opposing side walls of the separating elements.
  • the side walls have a fluidically favorable - straight and / or curved - course.
  • the upstream inflow geometry of the separating elements is also designed to be favorable in terms of flow.
  • the pulse channels have a rectangular cross-section.
  • the inlet cross sections of the pulse channels are about twice as large as their outlet cross sections.
  • the separating elements are covered to the housing interior through a thin top wall and so separated from the main flow to the rotors.
  • the top wall may extend axially parallel in the flow direction or follow the course of the wall of the compressor housing.
  • the pulse channels and separating elements have a height extending in the radial direction, which is at most twice as large as the width of the rotor gap.
  • the length of the pulse channels and dividers in the axial direction is between 10 and 100% of the length of the tendon at the rotor blade tip.
  • the pulse channels and separators terminate at a distance from the leading edge of the rotor blades whose size is between 10 and 100% of the length of the tendon at the rotor blade tip.
  • two or more pulse channels are provided for each rotor blade passage located between two rotor blades.
  • Fig. 1 shows an axial compressor used in a gas turbine engine having a plurality of assembled to a rotor drum and connected to a drive shaft 1 rotors 2 and arranged between the rotor blades 3, held on the compressor housing 4 stators 5.
  • the front rotor 2 is assigned upstream and at a distance from the existing between the blade tips and the compressor housing 4 rotor gap 6 a fixed to the inner wall of the compressor housing 4 flow pulse generator 7.
  • the flow pulse generator 7 is in a - compared to the main flow 8 -wandnahen Low flow rate region 9 is arranged at a distance A between the trailing edge 14 of the flow pulse generator 7 and the leading edge of the rotor blades 3.
  • the distance A and the length L of the flow pulse generator 7 amount to about 10 to 100% of the chord length measured at the blade tip S of the rotor blades 3.
  • the flow pulse generator 7 connects directly to the compressor housing 4, so that there is no air gap between them.
  • the height H of the flow pulse generator corresponds at most twice the value of the width B of the rotor gap 6.
  • the flow pulse generator 7 consists of a plurality of circumferentially spaced, tapered in the flow direction of the pulse channels 7a, which are provided by attached to the compressor housing 4, formed in accordance with the shape of the pulse channels 7a separating elements 7b.
  • two flow pulse generators 7, ie two pulse channels 7a are provided for each rotor blade passage 10.
  • three or four pulse channels 7a it is also possible for three or four pulse channels 7a to be assigned to a blade passage 10.
  • the cross-sectional area of the pulse channels 7a is preferably rectangular and the inlet cross section should be about twice as large as the outlet cross section.
  • the separating elements 7b and thus the pulse channels 7a are preferably shaped such that their course preferably follows the course of the compressor housing 4 follows.
  • the front edge 13 of the separating elements 7b is designed to be favorable in terms of flow.
  • the flow pulse generators 7 described above are easy to produce. There is no fear of wear or damage when the rotor blades 3 run in, and the compressor efficiency is not adversely affected by an increased fluid temperature.
  • the flow pulse can be adapted specifically to the respective flow conditions, so that the operating range of the axial compressor is widened and the surge limit is increased.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10007218.0A 2009-07-17 2010-07-13 Compresseur axial doté d'un générateur d'impulsions d'écoulement Withdrawn EP2292934A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009033754A DE102009033754A1 (de) 2009-07-17 2009-07-17 Axialverdichter mit einem Strömungsimpulserzeuger

Publications (2)

Publication Number Publication Date
EP2292934A2 true EP2292934A2 (fr) 2011-03-09
EP2292934A3 EP2292934A3 (fr) 2014-03-19

Family

ID=42676814

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10007218.0A Withdrawn EP2292934A3 (fr) 2009-07-17 2010-07-13 Compresseur axial doté d'un générateur d'impulsions d'écoulement

Country Status (3)

Country Link
US (1) US8591179B2 (fr)
EP (1) EP2292934A3 (fr)
DE (1) DE102009033754A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2976634B1 (fr) 2011-06-14 2013-07-05 Snecma Element de turbomachine
CN102306074B (zh) * 2011-09-19 2013-05-29 深圳莱宝高科技股份有限公司 电容式触控面板及其制作方法
CN102279686B (zh) * 2011-09-19 2013-06-19 深圳莱宝高科技股份有限公司 电容式触控面板及其制作方法
US20170045167A1 (en) * 2015-08-13 2017-02-16 Contech Engineered Solutions LLC Pipe joint for plastic pipes
CN111611743B (zh) * 2020-05-15 2023-03-28 上海上电电力工程有限公司 轴流式压气机特性线自适应方法

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
JPS5669404A (en) * 1979-11-07 1981-06-10 Hitachi Ltd Turbine blade train
DE3022206C2 (de) 1980-06-13 1983-08-11 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 4200 Oberhausen Axialverdichter mit verschobener Pumpgrenze
DE3308140C2 (de) * 1983-03-08 1985-12-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Mehrstufige Gasturbine
SU1666807A1 (ru) * 1989-07-19 1991-07-30 Харьковский авиационный институт им.Н.Е.Жуковского Осевой компрессор
EP0978633A1 (fr) * 1998-08-07 2000-02-09 Asea Brown Boveri AG Aube de turbomachine
DE10205363A1 (de) * 2002-02-08 2003-08-21 Rolls Royce Deutschland Gasturbine
RU2310101C2 (ru) * 2002-02-28 2007-11-10 Мту Аэро Энджинз Гмбх Компрессор (варианты) и вставка для корпуса компрессора (варианты)
DE102004030597A1 (de) * 2004-06-24 2006-01-26 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Aussenradstrahlerzeugung am Stator
GB2417053B (en) * 2004-08-11 2006-07-12 Rolls Royce Plc Turbine
DE102006048933A1 (de) 2006-10-17 2008-04-24 Mtu Aero Engines Gmbh Anordnung zur Strömungsbeeinflussung
US20100284795A1 (en) * 2007-12-28 2010-11-11 General Electric Company Plasma Clearance Controlled Compressor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Also Published As

Publication number Publication date
US8591179B2 (en) 2013-11-26
EP2292934A3 (fr) 2014-03-19
DE102009033754A1 (de) 2011-01-20
US20110014037A1 (en) 2011-01-20

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