EP0995039A1 - Compresseur centrifuge haute pression - Google Patents

Compresseur centrifuge haute pression

Info

Publication number
EP0995039A1
EP0995039A1 EP98966759A EP98966759A EP0995039A1 EP 0995039 A1 EP0995039 A1 EP 0995039A1 EP 98966759 A EP98966759 A EP 98966759A EP 98966759 A EP98966759 A EP 98966759A EP 0995039 A1 EP0995039 A1 EP 0995039A1
Authority
EP
European Patent Office
Prior art keywords
compressor
stage
centrifugal compressor
radial
rotating
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Withdrawn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
EP98966759A
Other languages
German (de)
English (en)
Inventor
David Lior
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.)
Technion Research and Development Foundation Ltd
Original Assignee
Technion Research and Development Foundation Ltd
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 Technion Research and Development Foundation Ltd filed Critical Technion Research and Development Foundation Ltd
Publication of EP0995039A1 publication Critical patent/EP0995039A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/127—Multi-stage pumps with radially spaced stages, e.g. for contrarotating type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means

Definitions

  • the outlet is increased 30 times over the air pressure in the inlet, the axial compressor
  • the current technology centrifugal compressor can attain pressure ratio of 1 :30 by
  • centrifugal compressor resulting in a pressure drop due to slowed air, decreased
  • the invention disclosed here is a multi stage centrifugal compressor including
  • a first stage centrifugal compressor having an axial inducer and a plurality of radial
  • a second stage centrifugal compressor including a rotating vanes disk
  • stage compressor having radial inlets.
  • centrifugal compressors where all stages have axial inducers and therefore require
  • the second stage rotor 6 has a
  • the relative Mach number of the flow in the second stage inlet 5 is
  • the compressed air leaving the outlet 7 of the second stage 6 has a high subsonic
  • vaneless diffuser 8 followed by a static vane diffuser 9 which is part of the housing.
  • the compressed air coming from diffuser 9 flows into a collector 10.
  • FIG. 1 shows a section in the plane of symmetry of the compressor of the
  • FIG. 2 is a front view of the compressor of Fig 1. showing its major parts
  • FIG. 3 shows a schematic section in the plane of symmetry containing the
  • Fig. 1 shows the major parts of the compressor of the present invention.
  • first stage centrifugal compressor rotor 1 is mounted on a shaft 11 which is supported
  • external power source (not shown) which can be a turbine powered shaft or other suitable external power source (not shown) which can be a turbine powered shaft or other suitable external power source (not shown) which can be a turbine powered shaft or other suitable external power source (not shown) which can be a turbine powered shaft or other suitable external power source (not shown) which can be a turbine powered shaft or other suitable external power source (not shown) which can be a turbine powered shaft or other suitable external power source (not shown) which can be a turbine powered shaft or other
  • a typical rotating speed is about 70,000 rpm.
  • a second stage compressor housing 15 attached to a second stage compressor vane disk 6 ( any single part shown in Fig 1 could represent several identical parts due to radial symmetry).
  • housing 15 and disk 6 rotate at
  • Housing 15 is mounted on shaft 11 by two
  • the left part of housing 15 is mounted on a left bearing 16 by a rotating
  • vane 17 which is used to direct the incoming air and may be used as pre compressor
  • First stage compressor rotor 1 sucks a gas such as air through an axial inducer
  • Second stage rotating vane disk 6 further compresses the air
  • diffuser 9 leaves diffuser 9 and flows into the collector 10.
  • Fig. 2 shows the compressing parts schematically from the front side.
  • shaft 11 is in the center line of the compressor encircled by axial inducer 2.
  • stage rotor 1 rotates around shaft 11, expelling compressed air into vaneless diffuser
  • Second compressor vanes disk 6 rotates in the same direction as rotor 1. Air
  • centrifugal compressor enters the vaneless diffuser 8 and later into the static vane
  • Fig 3. shows schematically how the new compressor of the present invention
  • a turbofan blade 23 forces the air into the engine where it passes a stator blade 24. Then, the air flow is divided into two flows. The outer flow moves through
  • stage 1 a second stage 6 which rotates at a different speed, and a diffuser 9.
  • present invention can be applied to multi stages centrifugal compressor in a single

Landscapes

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

Abstract

Ce compresseur centrifuge à plusieurs étages est constitué d'un premier étage (1), pourvu d'un aubage d'alimentation axial (2) et d'un certain nombre de sorties radiales (4), ainsi que d'un second étage (6) à disque rotatif à aubes (15) monté de manière à tourner co-axialement avec le premier étage (1). Ce second étage est pourvu d'entrées radiales (5).
EP98966759A 1997-07-08 1998-07-02 Compresseur centrifuge haute pression Withdrawn EP0995039A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
IL12125697A IL121256A0 (en) 1997-07-08 1997-07-08 High pressure centrifugal compressor
IL12125697 1997-07-08
PCT/IL1998/000310 WO1999002864A1 (fr) 1997-07-08 1998-07-02 Compresseur centrifuge haute pression

Publications (1)

Publication Number Publication Date
EP0995039A1 true EP0995039A1 (fr) 2000-04-26

Family

ID=11070355

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98966759A Withdrawn EP0995039A1 (fr) 1997-07-08 1998-07-02 Compresseur centrifuge haute pression

Country Status (4)

Country Link
EP (1) EP0995039A1 (fr)
AU (1) AU1550499A (fr)
IL (1) IL121256A0 (fr)
WO (1) WO1999002864A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
WO2006059994A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Ensemble de joint pour rotor de turbine-ventilateur de moteur de turbine a pression d’entree
WO2006059986A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Moteur a turbine de bout et procede de fonctionnement avec inversion de la circulation d'air du noyau du ventilateur
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
DE602004016065D1 (de) 2004-12-01 2008-10-02 United Technologies Corp Variable gebläseeinlassleitschaufelanordnung, turbinenmotor mit solch einer anordnung und entsprechendes steuerverfahren

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE706213C (de) * 1938-09-10 1941-05-21 Alessandro Tebaldi Fliehkraftverdichter
FR908121A (fr) * 1943-12-15 1946-04-01 Perfectionnements aux machines rotatives à circulation de fluide, telles que compresseurs ou turbines, et à dispositifs variateurs de cette circulation
DE1110810B (de) * 1956-01-19 1961-07-13 Licentia Gmbh Gegenlauf-Verdichter oder -Pumpe
FR1203887A (fr) * 1958-07-04 1960-01-21 Snecma Perfectionnements aux compresseurs centrifuges
US3941501A (en) * 1974-11-18 1976-03-02 Avco Corporation Diffuser including a rotary stage
US4449888A (en) * 1982-04-23 1984-05-22 Balje Otto E Free spool inducer pump
CH678352A5 (fr) * 1988-06-23 1991-08-30 Sulzer Ag
GB9127474D0 (en) * 1991-12-30 1992-02-19 Framo Dev Ltd Multiphase fluid transport

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9902864A1 *

Also Published As

Publication number Publication date
WO1999002864A1 (fr) 1999-01-21
IL121256A0 (en) 1998-01-04
AU1550499A (en) 1999-02-08

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