WO2016160393A1 - Diffuseur ayant de multiples rangées d'aubes de diffuseur avec une solidité différente - Google Patents

Diffuseur ayant de multiples rangées d'aubes de diffuseur avec une solidité différente Download PDF

Info

Publication number
WO2016160393A1
WO2016160393A1 PCT/US2016/023388 US2016023388W WO2016160393A1 WO 2016160393 A1 WO2016160393 A1 WO 2016160393A1 US 2016023388 W US2016023388 W US 2016023388W WO 2016160393 A1 WO2016160393 A1 WO 2016160393A1
Authority
WO
WIPO (PCT)
Prior art keywords
row
vanes
diffuser
compressor
process fluid
Prior art date
Application number
PCT/US2016/023388
Other languages
English (en)
Inventor
James Sorokes
Mark J. Kuzdzal
Paul Morrison Brown
Silvano R. Saretto
Ravichandra SRINIVASAN
Logan SAILER
Original Assignee
Dresser-Rand Company
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 Dresser-Rand Company filed Critical Dresser-Rand Company
Publication of WO2016160393A1 publication Critical patent/WO2016160393A1/fr

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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • 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
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • Embodiments of the disclosure may further provide a compressor.
  • the compressor may include a housing and an inlet coupled to or integral with the housing and defining an inlet passageway configured to receive and flow a process fluid the rethrough.
  • the compressor may also include a rotary shaft configured to be driven by a driver, and a centrifugal impeller mounted about the rotary shaft and fluidly coupled to the inlet passageway.
  • the centrifugal impeller may be configured to rotate about a center axis and impart energy to the process fluid received via the inlet passageway.
  • the compressor may further include a static diffuser circumferentially disposed about the centrifugal impeller and configured to receive the process fluid from the centrifugal impeller and convert the energy imparted to pressure energy.
  • the compression system 100 may compress the process fluid to a compression ratio of about 6:1 , about 6.1 :1 , about 6.2:1 , about 6.3:1 , about 6.4:1 , about 6.5:1 , about 6.6:1 , about 6.7:1 , about 6.8:1 , about 6.9:1 , about 7:1 , about 7.1 :1 , about 7.2:1 , about 7.3:1 , about 7.4:1 , about 7.5:1 , about 7.6:1 , about 7.7:1 , about 7.8:1 , about 7.9:1 , about 8:1 , about 8.1 :1 , about 8.2:1 , about 8.3:1 , about 8.4:1 , about 8.5:1 , about 8.6:1 , about 8.7:1 , about 8.8:1 , about 8.9:1 , about 9:1 , about 9.1 :1 , about 9.2:1 , about 9.3:1 , about
  • the compressor 102 may include one or more stages (not shown). In at least one embodiment, the compressor 102 may be a single-stage compressor. In another embodiment, the compressor 102 may be a multi-stage centrifugal compressor. Each stage (not shown) of the compressor 102 may be a subsonic compressor stage or a supersonic compressor stage. In an exemplary embodiment, the compressor 102 may include a single supersonic compressor stage. In another embodiment, the compressor 102 may include a plurality of subsonic compressor stages. In yet another embodiment, the compressor 102 may include a subsonic compressor stage and a supersonic compressor stage. Any one or more stages of the compressor 102 may have a compression ratio greaterthan about 1 :1 .
  • FIG. 2A illustrates a cross-sectional view of an embodiment of the compressor 102, which may be included in the compression system 100 of Figure 1 .
  • Figure 2B illustrates an enlarged view of the portion of the compressor 102 indicated by the box labeled 2B of Figure 2A, according to one or more embodiments disclosed.
  • the compressor 102 includes a housing 1 10 forming or having an axial inlet 1 12 defining an inlet passageway 1 14, a static diffuser 1 16 fluidly coupled to the inlet passageway 1 14, and a collector 1 17 fluidly coupled to the static diffuser 1 16.
  • the inlet 1 12 may be a radial inlet.
  • the driver 104 may be disposed outside of (as shown in Figure 1) or within the housing 1 10, such that the housing 1 10 may have a first end, or compressor end, and a second end (not shown) , or driver end.
  • the housing 1 10 may be configured to hermetically seal the driver 104 and the compressor 102 within, thereby providing both support and protection to each component of the compression system 100.
  • the housing 1 10 may also be configured to contain the process fluid flowing through one or more portions or components of the compressor 102.
  • the compressor 102 may include a balance piston 142 configured to balance an axial thrust generated by the centrifugal impeller 126 during operation.
  • the balance piston 142 may be integral with the centrifugal impeller 126, such that the balance piston 142 and the centrifugal impeller 126 are formed from a single or unitary piece.
  • the balance piston 142 and the centrifugal impeller 126 may be separate components.
  • the balance piston 142 and the centrifugal impeller 126 may be separate annular components coupled with one another.
  • One or more seals e.g. , labyrinth seals, may be implemented to isolate the balance piston 142 from external contaminants or lubricants.
  • the process fluid at the tip 136 of the centrifugal impeller 126 may be supersonic and have an exit absolute Mach number of one or greater.
  • the process fluid at the tip 136 of the centrifugal impeller 126 may have an exit absolute Mach number of at least one, at least 1 .1 , at least 1 .2, at least 1 .3, at least 1 .4, or at least 1 .5.
  • the compressor 102 discussed herein may be "supersonic," as the centrifugal impeller 126 may be configured to rotate about the center axis 128 at a speed sufficient to provide the process fluid at the tip 136 thereof with an exit absolute Mach number of one or greater or with a fluid velocity greater than the speed of sound.
  • the rotational or tip speed of the centrifugal impeller 126 may be about 500 meters per second (m/s) or greater.
  • the blades 144a,b of the centrifugal impeller 126 may be curved, such that the process fluid may be urged in a tangential and radial direction by the centrifugal force through a plurality of flow passages formed by the blades 144a, b and discharged from the blade tips of the centrifugal impeller 126 (cumulatively, the tip 136 of the centrifugal impeller 126) in at least partially radial directions that extend 360 degrees around the centrifugal impeller 126.
  • the contour or amount of curvature of the blades 144a,b is not limited to the shaping illustrated in Figure 3 and may be determined based, at least in part, on desired operating parameters.
  • the splitter blades 144b and main blades 144a may be arranged circumferentially about the center axis 128 in a pattern such that a splitter blade 144b is disposed between adjacent main blades 144a. As arranged, the splitter blades 144b may be "clocked" with respect to the main blades 144a, such that each splitter blade 144b is circumferentially offset or not equidistant from the respective adjacent main blades 144a and thus is not circumferentially centered between the adjacent main blades 144a. By clocking the splitter blades 144b, e.g.
  • the second row vanes 186 may have a greater solidity than the first row vanes 184, where the chord to pitch ratio of the second row vanes 186 is greater than the chord to pitch ratio of the first row vanes 184.
  • the chord to pitch ratio of the second row vanes 186 is one or greater.
  • diffuser vanes having a chord to pitch ratio of one or greater are referred to as high solidity diffuser vanes.
  • the second ring 190 may include a multiple of the number of first row vanes 184, and more specifically, twice the number of first row vanes 184.
  • the first row vanes 184 of the first ring 188 may be proximal the tip 136 of the centrifugal impeller 126 and may be spaced therefrom via a n inner vaneless space 200. Accordingly, the inner vaneless space 200 may be provided between the centrifugal impeller tip diameter 202 and the leading edge diameter 204 of the first ring 188. In an exemplary embodiment, the inner vaneless space 200 may be formed from the leading edge diameter 204 being about five to about ten percent greater than the centrifugal impeller tip diameter 202. In another embodiment, the inner vaneless space 200 may be formed from the leading edge diameter 204 being about six to about eight percent greater than the centrifugal impeller tip diameter 202.
  • an outer vaneless space 206 may be provided between the diameter 208 formed by the trailing edges 194 of the first row vanes 184 of the first ring 188 and the diameter 21 O of the leading edges 196 of the second row vanes 186 of the second ring 190.
  • the outer vaneless space 206 may be formed from the leading edge diameter 210 of the second ring 190 being about five to about ten percent greater than the trailing edge diameter 208 of the first ring 188.
  • the outer vaneless space 206 may be formed from the leading edge diameter 210 of the second ring 190 being about six to about eight percent greater than the trailing edge diameter 208 of the first ring 188.
  • the incidence of the second row vanes 186 of the second ring 190 may be determined by placing the second ring 190 in the "shadow" or flow path of the first ring 188. Accordingly, the second row vanes 186 may be arranged such that two second row vanes 186 are provided in the wake of each first row vane 184 and are provided to alter the direction of the process fluid flow.
  • the static diffuser 1 16 may include third row vanes (not shown) arranged in a third ring (not shown) about the center axis 128 and disposed radially outward of the first ring 188 and the second ring 190, where the first ring 188, the second ring 190, and the third ring are concentric.
  • the third row vanes may have a chord to pitch ratio less than the chord to pitch ratio of the second row vanes 186 of the second ring 190.
  • the third row vanes may have a chord to pitch ratio substantially equal to the chord to pitch ratio of the first row vanes 184 of the first ring 188.
  • the third row vanes may be configured to provide additional turning of the process fluid flow.
  • the process fluid pressurized, circulated, contained, or otherwise utilized in the compression system 100 may be a fluid in a liquid phase, a gas phase, a supercritical state, a subcritical state, or any combination thereof.
  • the process fluid may be a mixture, or process fluid mixture.
  • the process fluid may include one or more high molecular weight process fluids, one or more low molecular weight process fluids, or any mixture or combination thereof.
  • high molecular weight process fluids refers to process fluids having a molecular weight of about 30 grams per mole (g/mol) or greater.

Abstract

L'invention concerne un diffuseur pour un compresseur, lequel diffuseur comprend un passage de diffuseur annulaire défini par une paroi de moyeu et une paroi de carénage d'un carter du compresseur. Le passage de diffuseur annulaire peut être couplé fluidiquement à un rotor centrifuge conçu de façon à tourner avec un arbre rotatif du compresseur autour d'un axe central. Le diffuseur peut également comprendre une pluralité d'aubes de diffuseur à faible solidité s'étendant dans le passage de diffuseur annulaire à partir de la paroi de moyeu ou de la paroi de carénage, et disposées de manière annulaire autour de l'axe central. Le diffuseur peut en outre comprendre une pluralité d'aubes de diffuseur à solidité élevée disposées radialement vers l'extérieur à partir de la pluralité d'aubes de diffuseur à faible solidité et s'étendant dans le passage de diffuseur annulaire à partir de la paroi de moyeu ou de la paroi de carénage, et disposées de manière annulaire autour de l'axe central.
PCT/US2016/023388 2015-03-27 2016-03-21 Diffuseur ayant de multiples rangées d'aubes de diffuseur avec une solidité différente WO2016160393A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201562139033P 2015-03-27 2015-03-27
US62/139,033 2015-03-27

Publications (1)

Publication Number Publication Date
WO2016160393A1 true WO2016160393A1 (fr) 2016-10-06

Family

ID=57005299

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2016/023388 WO2016160393A1 (fr) 2015-03-27 2016-03-21 Diffuseur ayant de multiples rangées d'aubes de diffuseur avec une solidité différente

Country Status (1)

Country Link
WO (1) WO2016160393A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170298942A1 (en) * 2016-04-19 2017-10-19 Honda Motor Co., Ltd. Compressor
WO2019160550A1 (fr) * 2018-02-15 2019-08-22 Dresser-Rand Company Compresseur centrifuge permettant d'obtenir un taux de compression élevé
EP3540236A1 (fr) * 2018-03-16 2019-09-18 Carrier Corporation Compresseur à flux mixte de système de réfrigération
US20230037793A1 (en) * 2021-08-09 2023-02-09 Turbowin Co., Ltd. Air compressing apparatus with bearing wear-causing thrust reducing/compensating unit

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4877370A (en) * 1987-09-01 1989-10-31 Hitachi, Ltd. Diffuser for centrifugal compressor
US5152661A (en) * 1988-05-27 1992-10-06 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
JPH05133396A (ja) * 1991-11-13 1993-05-28 Hitachi Ltd 遠心形流体機械のデイフユーザ
US5709531A (en) * 1993-04-28 1998-01-20 Hitachi, Ltd. Centrifugal compressor and vaned diffuser
JP2008095638A (ja) * 2006-10-13 2008-04-24 Mitsubishi Heavy Ind Ltd 斜流圧縮機

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4877370A (en) * 1987-09-01 1989-10-31 Hitachi, Ltd. Diffuser for centrifugal compressor
US5152661A (en) * 1988-05-27 1992-10-06 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
JPH05133396A (ja) * 1991-11-13 1993-05-28 Hitachi Ltd 遠心形流体機械のデイフユーザ
US5709531A (en) * 1993-04-28 1998-01-20 Hitachi, Ltd. Centrifugal compressor and vaned diffuser
JP2008095638A (ja) * 2006-10-13 2008-04-24 Mitsubishi Heavy Ind Ltd 斜流圧縮機

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170298942A1 (en) * 2016-04-19 2017-10-19 Honda Motor Co., Ltd. Compressor
US10393143B2 (en) * 2016-04-19 2019-08-27 Honda Motor Co., Ltd. Compressor with annular diffuser having first vanes and second vanes
WO2019160550A1 (fr) * 2018-02-15 2019-08-22 Dresser-Rand Company Compresseur centrifuge permettant d'obtenir un taux de compression élevé
EP3540236A1 (fr) * 2018-03-16 2019-09-18 Carrier Corporation Compresseur à flux mixte de système de réfrigération
CN110273858A (zh) * 2018-03-16 2019-09-24 开利公司 制冷系统混流式压缩机
US11421708B2 (en) 2018-03-16 2022-08-23 Carrier Corporation Refrigeration system mixed-flow compressor
CN110273858B (zh) * 2018-03-16 2023-05-02 开利公司 制冷系统混流式压缩机
US20230037793A1 (en) * 2021-08-09 2023-02-09 Turbowin Co., Ltd. Air compressing apparatus with bearing wear-causing thrust reducing/compensating unit

Similar Documents

Publication Publication Date Title
US20160281732A1 (en) Impeller with offset splitter blades
US10240613B2 (en) Supersonic compressor with structural arrangement to increase pressure energy in a discharge process fluid received from a centrifugal impeller
US20160281727A1 (en) Apparatus, system, and method for compressing a process fluid
US7293955B2 (en) Supersonic gas compressor
US7334990B2 (en) Supersonic compressor
RU2581686C2 (ru) Радиальная диффузорная лопатка для центробежных компрессоров
US10584709B2 (en) Electrically heated balance piston seal
CN105782073B (zh) 多级径向压缩机挡板
JP6087351B2 (ja) 多段遠心ターボ機械
US9567864B2 (en) Centrifugal impeller and turbomachine
US10221858B2 (en) Impeller blade morphology
US20170314572A1 (en) Impeller shroud for a compressor
WO2016160393A1 (fr) Diffuseur ayant de multiples rangées d'aubes de diffuseur avec une solidité différente
CN109252900B (zh) 一种复合式透平
US20170002825A1 (en) Balance piston with a sealing member
CN111120400A (zh) 一种用于微型燃机的离心压气机
WO2004099588A2 (fr) Compresseur supersonique
US20170350417A1 (en) Variable area diffuser
EP3274591B1 (fr) Compresseur avec un systéme de centrage d'un joint de piston d'équilibrage
US20180058261A1 (en) Turbine
CN112096460B (zh) 径流式透平膨胀机结构
JP2019100200A (ja) 多段遠心圧縮機、ケーシング及びリターンベーン
KR20220015700A (ko) 블레이드와 이를 포함하는 압축기 및 가스 터빈

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 16773741

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 16773741

Country of ref document: EP

Kind code of ref document: A1