[go: up one dir, main page]

WO1999002864A1 - Compresseur centrifuge haute pression - Google Patents

Compresseur centrifuge haute pression Download PDF

Info

Publication number
WO1999002864A1
WO1999002864A1 PCT/IL1998/000310 IL9800310W WO9902864A1 WO 1999002864 A1 WO1999002864 A1 WO 1999002864A1 IL 9800310 W IL9800310 W IL 9800310W WO 9902864 A1 WO9902864 A1 WO 9902864A1
Authority
WO
WIPO (PCT)
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.)
Ceased
Application number
PCT/IL1998/000310
Other languages
English (en)
Other versions
WO1999002864B1 (fr
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
Priority to EP98966759A priority Critical patent/EP0995039A1/fr
Priority to AU15504/99A priority patent/AU1550499A/en
Publication of WO1999002864A1 publication Critical patent/WO1999002864A1/fr
Publication of WO1999002864B1 publication Critical patent/WO1999002864B1/fr
Anticipated expiration legal-status Critical
Ceased 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).
PCT/IL1998/000310 1997-07-08 1998-07-02 Compresseur centrifuge haute pression Ceased WO1999002864A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP98966759A EP0995039A1 (fr) 1997-07-08 1998-07-02 Compresseur centrifuge haute pression
AU15504/99A AU1550499A (en) 1997-07-08 1998-07-02 High pressure centrifugal compressor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IL12125697A IL121256A0 (en) 1997-07-08 1997-07-08 High pressure centrifugal compressor
IL121256 1997-07-08

Publications (2)

Publication Number Publication Date
WO1999002864A1 true WO1999002864A1 (fr) 1999-01-21
WO1999002864B1 WO1999002864B1 (fr) 1999-02-25

Family

ID=11070355

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IL1998/000310 Ceased WO1999002864A1 (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)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US7631485B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Tip turbine engine with a heat exchanger
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (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
FR1203887A (fr) * 1958-07-04 1960-01-21 Snecma Perfectionnements aux compresseurs centrifuges
DE1110810B (de) * 1956-01-19 1961-07-13 Licentia Gmbh Gegenlauf-Verdichter oder -Pumpe
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
EP0348342A1 (fr) * 1988-06-23 1989-12-27 GebràœDer Sulzer Aktiengesellschaft Machine centrifuge à roues à aubes contrarotives
US5580214A (en) * 1991-12-30 1996-12-03 Framo Developments (Uk) Limited Multiphase fluid treatment

Patent Citations (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
EP0348342A1 (fr) * 1988-06-23 1989-12-27 GebràœDer Sulzer Aktiengesellschaft Machine centrifuge à roues à aubes contrarotives
US5580214A (en) * 1991-12-30 1996-12-03 Framo Developments (Uk) Limited Multiphase fluid treatment

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US7631485B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Tip turbine engine with a heat exchanger
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method

Also Published As

Publication number Publication date
EP0995039A1 (fr) 2000-04-26
IL121256A0 (en) 1998-01-04
AU1550499A (en) 1999-02-08

Similar Documents

Publication Publication Date Title
US8950171B2 (en) Counter-rotating gearbox for tip turbine engine
US5105616A (en) Gas turbine with split flow radial compressor
US4968216A (en) Two-stage fluid driven turbine
EP1921290B1 (fr) Assemblage de moteur de réacteur à double flux
US4428715A (en) Multi-stage centrifugal compressor
US3673802A (en) Fan engine with counter rotating geared core booster
EP1825111B1 (fr) Carter de compresseur à rotation inverse pour un moteur à turbine en bout
US7293955B2 (en) Supersonic gas compressor
US8104257B2 (en) Tip turbine engine with multiple fan and turbine stages
US3868196A (en) Centrifugal compressor with rotating vaneless diffuser powered by leakage flow
EP2428648B1 (fr) Moteur de turbine à gaz
KR20100138843A (ko) 초음속 압축기, 초음속 압축기 로터 및 유체 압축 방법
JPH079194B2 (ja) ガスタービン・エンジンの冷却空気転送手段
US3357176A (en) Twin spool gas turbine engine with axial and centrifugal compressors
US3941501A (en) Diffuser including a rotary stage
EP0995039A1 (fr) Compresseur centrifuge haute pression
US3305165A (en) Elastic fluid compressor
US10480519B2 (en) Hybrid compressor
US4661042A (en) Coaxial turbomachine
US4303377A (en) Turbine-compressor ejector
CA1153212A (fr) Turbomoteur a gaz
EP0021709A1 (fr) Compresseur centrifuge multicellulaire et son application à une turbine
JP2530526B2 (ja) ２つの流体を同時に圧縮するためのタ―ボポンプ
US20040151579A1 (en) Supersonic gas compressor
WO1999002864B1 (fr) Compresseur centrifuge haute pression

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AL AM AT AU AZ BA BB BG BR BY CA CH CN CU CZ DE DK EE ES FI GB GE GH GM GW HR HU ID IL IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MD MG MK MN MW MX NO NZ PL PT RO RU SD SE SG SI SK SL TJ TM TR TT UA UG US UZ VN YU ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): GH GM KE LS MW SD SZ UG ZW AM AZ BY KG KZ MD RU TJ TM AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE BF BJ CF CG CI CM GA GN ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
WWE Wipo information: entry into national phase

Ref document number: 09446843

Country of ref document: US

NENP Non-entry into the national phase

Ref country code: KR

WWE Wipo information: entry into national phase

Ref document number: 1998966759

Country of ref document: EP

WWP Wipo information: published in national office

Ref document number: 1998966759

Country of ref document: EP

REG Reference to national code

Ref country code: DE

Ref legal event code: 8642

NENP Non-entry into the national phase

Ref country code: CA

WWW Wipo information: withdrawn in national office

Ref document number: 1998966759

Country of ref document: EP