EP0042044A1 - Compresseur axial dont la limite de pompage est déplacée - Google Patents

Compresseur axial dont la limite de pompage est déplacée Download PDF

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Publication number
EP0042044A1
EP0042044A1 EP81102534A EP81102534A EP0042044A1 EP 0042044 A1 EP0042044 A1 EP 0042044A1 EP 81102534 A EP81102534 A EP 81102534A EP 81102534 A EP81102534 A EP 81102534A EP 0042044 A1 EP0042044 A1 EP 0042044A1
Authority
EP
European Patent Office
Prior art keywords
axial compressor
compressor according
flow
housing
sleepers
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
EP81102534A
Other languages
German (de)
English (en)
Other versions
EP0042044B1 (fr
Inventor
Hartmut Dr.-Ing. Griepentrog
Hellmut Weinrich
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.)
MAN Energy Solutions SE
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg 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 MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Publication of EP0042044A1 publication Critical patent/EP0042044A1/fr
Application granted granted Critical
Publication of EP0042044B1 publication Critical patent/EP0042044B1/fr
Expired 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
    • 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
    • F04D29/545—Ducts
    • F04D29/547—Ducts having a special shape in order to influence fluid flow

Definitions

  • the invention relates to a single-stage or multi-stage axial compressor with axially one behind the other, combined into stages guide vane and rotor blade rings, and with one or more protruding from the inner surface of the housing surrounding the vane rings, circumferential around the axis, the type of a threshold Stairs are graduated.
  • Such a device is described in DE-PS 809 842.
  • the changes in the inside diameter required in the direction of flow are carried out in this device by gradual narrowing.
  • the thresholds mentioned are present both on the inside of the housing and on the outside of the rotor.
  • the threshold surfaces are preferably each cylindrical or conical.
  • the flow guidance is to be improved by the thresholds in such a way that the risk of the flow separating at the impeller outside and at the stator inside is reduced when the axial speed is shifted.
  • Such a shift in the axial speed is then - according to the cited patent - under certain circumstances forced to avoid difficulties with regard to the Mach number at high peripheral speeds. This indicates that the known device should make it possible to improve the flow, particularly when shifting to high speeds.
  • the primary aim is not to improve the design of the compressor, but to enlarge the working area. As experience shows, it is necessary to increase the flow in the axial direction at the blade tip if, for. B. the peripheral speed is reduced.
  • DE-AS 2 351 308 To avoid the stall, it is also known (DE-AS 2 351 308) to arrange a profiled ring which is arranged in front of a rotor blade ring and is concentric with the machine axis, the outer ring surface of which forms an annular channel converging in the flow direction with the housing wall.
  • the proposed solution according to DE-AS 2 351 308 is indeed feasible, but in practice means relatively high additional construction costs, since the ring can be difficult to install in the housing if the other structural requirements are taken into account. The efficiency losses due to the additional, friction-generating surface and the so-called flow wake are also not to be underestimated.
  • the construction according to the invention therefore has the advantages that it can be installed economically and at a reasonable cost, and that, in theory, it causes only a slight loss in efficiency which could not be measured in practice.
  • the device according to DE-OS 2 446 512 is unsuitable in the case of the axially compressed type mentioned at the beginning of the invention, in order to stabilize the surge limit in the lower delivery range, in particular because the detachment that first occurs on the rotor blade grille cannot be corrected, but also on the other hand Because of the completely different blade configuration of a compressor with axial blading, the principle is not transferable.
  • An essential criterion for the design of the object according to the invention is that, under normal load, the sleepers to be installed do not narrow the cross section so much that normal operation is significantly impeded.
  • the sleepers should preferably constrict the free overall cross-section of the housing only to an amount between 80-99%, preferably between 95-99%, of the cross-sectional area existing before the threshold.
  • the inner contour of the compressor housing can be assigned a certain average taper, which is related to the compression to be achieved. It is proposed, when using the sleepers according to the invention, to approximate the base points of the sleepers to a conical jacket describing the mean taper of the inner wall of the housing It is also possible to deviate from this position, whereby wind tunnel and standing tests can provide the expert with hints for improvement.
  • the threshold height can then preferably also be varied in the further course of the flow, in particular increasing successively.
  • the exemplary embodiments of multi-stage axial compressors shown in FIGS. 1 and 2 have guide vane and rotor blade rings arranged one after the other and combined to form stages 1, 2, 3.
  • the guide blades 4, 6 are connected downstream of the moving blades 5, 7.
  • a guide ring 8 with pivotable blades for regulating the throughput quantity is arranged in front of the first rotor blade ring.
  • the blades 4 to 7 are also partially pivotable and connected to corresponding adjustment devices.
  • sleepers 12, 13, 14 are provided on the opposite inner wall 11 of the housing, which protrude inward and circumferentially around the axis from the inner surface of the housing surrounding the blade rings.
  • the sleepers are stepped in the direction of flow in the manner of a staircase, constricting the free overall cross-section of the housing from step to step by 1-5% of the cross-sectional area in front of the threshold.
  • Each threshold 12 - 14 is arranged directly in front of a moving blade, in the present case designated with the numbers 15, 16, 17, the streamlines being compressed in operation in the area of the moving blade tips.
  • the outer contour of the sleepers i. H. the rising surface 18 rounded convex curved.
  • the curve of curvature is composed of circular and / or parabolic arcs. The curvature is intended to prevent flow breaks, turbulence and similar disturbances in the flow from occurring.
  • the narrowing of the overall cross section through the thresholds 12, 13, 14 is not so great that an excessive flow constriction occurs in normal operation, which is also undesirable.
  • FIG. 4 shows various characteristic curves which were measured on an axial compressor with an output of approximately 400,000 m 3 / h.
  • the flow channel with a tapered but smooth inner surface was used once; on the other hand, a flow channel was used which had the thresholds according to the invention.
  • the design point for both compressors was a pressure ratio of approximately 4.4 and a nominal delivery rate of approximately 375,000 m 3 / h.
  • the surge limit in the original form, designated G1 was significantly less favorable than when using sleepers according to the invention. This resulted in a curve G2.
  • the characteristic curves a ... f were measured at different guide vane positions, the percentages relating to the adjustment range of the guide vanes, ie defined by the path of the vane adjustment mechanism.
  • the nominal speed was around 3,000 rpm.
  • the base points of the thresholds 12-14 each lie on one medium conicity of the conical casing describing the inner wall of the housing. This shape is relatively easy to manufacture and brings a defined compression performance.
  • the blades In order to allow the blades to be precisely fitted within the housing, the blades are turned over at their tips in a cylindrical or conical manner. This gives them exactly the same distance from the inner wall of the housing, the gradation through the threshold allowing a defined flow gain that is the same for all individual blades.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP81102534A 1980-06-13 1981-04-03 Compresseur axial dont la limite de pompage est déplacée Expired EP0042044B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3022206A DE3022206C2 (de) 1980-06-13 1980-06-13 Axialverdichter mit verschobener Pumpgrenze
DE3022206 1980-06-13

Publications (2)

Publication Number Publication Date
EP0042044A1 true EP0042044A1 (fr) 1981-12-23
EP0042044B1 EP0042044B1 (fr) 1984-07-11

Family

ID=6104545

Family Applications (1)

Application Number Title Priority Date Filing Date
EP81102534A Expired EP0042044B1 (fr) 1980-06-13 1981-04-03 Compresseur axial dont la limite de pompage est déplacée

Country Status (4)

Country Link
EP (1) EP0042044B1 (fr)
JP (2) JPS5728900A (fr)
DE (2) DE3022206C2 (fr)
SU (1) SU1109065A3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8591179B2 (en) 2009-07-17 2013-11-26 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor with a flow pulse generator
US8677757B2 (en) 2009-07-08 2014-03-25 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber head of a gas turbine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2908152B1 (fr) * 2006-11-08 2009-02-06 Snecma Sa Aube en fleche de turbomachine
JP6423084B2 (ja) 2014-08-29 2018-11-14 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ ガスタービンエンジン用の制御された収束圧縮機流路

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH216489A (de) * 1940-04-04 1941-08-31 Sulzer Ag Mehrstufiger Axialverdichter.
DE809842C (de) * 1948-10-19 1951-08-02 Hermann Oestrich Dr Ing Axialverdichter
US2846137A (en) * 1955-06-03 1958-08-05 Gen Electric Construction for axial-flow turbomachinery
GB866793A (en) * 1956-09-01 1961-05-03 Gio Batta Sommariva Improvements in or relating to axial flow compressors
DE1428077A1 (de) * 1963-03-20 1969-03-20 Donezkij G Pk I Exi Komplexnoi Axialluefter
US3775023A (en) * 1971-02-17 1973-11-27 Teledyne Ind Multistage axial flow compressor

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990106A (en) * 1956-10-12 1961-06-27 English Electric Co Ltd Axial flow multi-stage compressors
DE2351308C3 (de) * 1973-10-12 1981-10-08 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 4200 Oberhausen Einrichtung zur Erweiterung des Arbeitsbereichs von Axialströmungsmaschinen
JPS5314205A (en) * 1976-07-23 1978-02-08 Hitachi Ltd Step structure for axial-flow fluid machine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH216489A (de) * 1940-04-04 1941-08-31 Sulzer Ag Mehrstufiger Axialverdichter.
DE809842C (de) * 1948-10-19 1951-08-02 Hermann Oestrich Dr Ing Axialverdichter
US2846137A (en) * 1955-06-03 1958-08-05 Gen Electric Construction for axial-flow turbomachinery
GB866793A (en) * 1956-09-01 1961-05-03 Gio Batta Sommariva Improvements in or relating to axial flow compressors
DE1428077A1 (de) * 1963-03-20 1969-03-20 Donezkij G Pk I Exi Komplexnoi Axialluefter
US3775023A (en) * 1971-02-17 1973-11-27 Teledyne Ind Multistage axial flow compressor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8677757B2 (en) 2009-07-08 2014-03-25 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber head of a gas turbine
US8591179B2 (en) 2009-07-17 2013-11-26 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor with a flow pulse generator

Also Published As

Publication number Publication date
EP0042044B1 (fr) 1984-07-11
DE3022206A1 (de) 1982-01-07
JPS5728900A (en) 1982-02-16
JPS6259800U (fr) 1987-04-14
DE3022206C2 (de) 1983-08-11
DE3164670D1 (en) 1984-08-16
SU1109065A3 (ru) 1984-08-15

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