EP1873402A1 - Abgasturbolader mit einem Radialverdichter - Google Patents

Abgasturbolader mit einem Radialverdichter Download PDF

Info

Publication number
EP1873402A1
EP1873402A1 EP06013164A EP06013164A EP1873402A1 EP 1873402 A1 EP1873402 A1 EP 1873402A1 EP 06013164 A EP06013164 A EP 06013164A EP 06013164 A EP06013164 A EP 06013164A EP 1873402 A1 EP1873402 A1 EP 1873402A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
compressor
leading edge
flow direction
impeller
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Withdrawn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
EP06013164A
Other languages
English (en)
French (fr)
Inventor
Paul Dr. Roach
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.)
Napier Turbochargers Ltd
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP06013164A priority Critical patent/EP1873402A1/de
Publication of EP1873402A1 publication Critical patent/EP1873402A1/de
Withdrawn legal-status Critical Current

Links

Images

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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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

  • the present invention relates to a compressor, in particular to a compressor for a turbocharger, as it is for example used with an internal combustion engine.
  • Such compressors comprise of an impeller with an impeller exit, and a diffuser with a number of diffuser vanes.
  • the leading edges of the diffuser vanes face towards a flow direction in which a compressible fluid flows through the compressor.
  • the diffuser vanes are oriented perpendicular to the flow direction of the compressed medium as it is, e.g., shown in US 5,641,860 .
  • compressor diffuser vanes with inclined leading edges are also known from KR 2002 084613 , where the leading edges are inclined with respect to the direction perpendicular to the flow direction by 15 to 20 degrees.
  • the invented compressor comprises an impeller and a diffuser with a number of diffuser vanes.
  • the diffuser is located downstream of the impeller, each diffuser vane having a leading edge facing the flow direction, but is cut back.
  • the cut back region is at least locally inclined with respect to the flow direction by an angle of no more than 65 degrees. It may extend over the whole leading edge or only over a part of the leading edge.
  • Compressor diffuser vanes usually have leading edges which extend perpendicular to the flow direction, or with an angle above 70 degrees to the flow direction. Such leading edges lead to flow separation due to high angle of incidence of the flow, which leads to significant loss of stage efficiency, and a reduced operating range.
  • a suitably cut back leading edge overcomes the tendency of the flow to separate in the region of the leading edges. It has been found by the inventor that an inclination angle of not more than 65 degrees with respect to the flow direction has a very positive impact on the diffuser performance, preventing the tendency to separate over the whole range of operation. As a result, the operating range of the compressor is significantly increased, as is its peak efficiency.
  • the cut back region may be formed by a linear edge section.
  • Linear edge sections are most easily manufactured, so that the effort for implementing the invention can be minimised.
  • the linear edge section may in particular extend over the whole of the leading edge.
  • the cut back region may take the form of a curve. Again, the curved profile may extend over the whole of the leading edge.
  • the leading edge takes the form of a dovetail structure.
  • the diffuser vanes are located between diffuser end-walls.
  • the cut back region may be deepest at the wall. This implementation is particularly effective in reducing the tendency of the flow to separate at the leading edges.
  • the invented turbocharger includes the inventive compressor. As with the inventive compressor, the performance of the turbocharger will also be increased.
  • Figure 1 shows a first embodiment of the inventive compressor.
  • Figure 1A shows a detail of Figure 1.
  • Figure 2 shows a second embodiment of the inventive compressor.
  • Figure 2A shows a detail of Figure 2.
  • Figure 3 shows a third embodiment of the inventive compressor.
  • Figure 3A shows a detail of Figure 3.
  • Figure 4 shows a fourth embodiment of the inventive compressor.
  • Figure 4A shows a detail of Figure 4.
  • Figure 5 shows a diagram of the diffuser pressure recovery as a function of the leading edge sweep angle in the first embodiment of the invention.
  • Figure 6 visualises the flow of the fluid in a diffuser with conventional diffuser vanes.
  • Figure 7 visualises the flow of the fluid in a diffuser according to the invention.
  • Figure 8 shows a comparison of compressor characteristics between a compressor with conventional diffuser vanes and those according to the invention.
  • FIG. 1A A first embodiment of the inventive compressor will now be described with reference to Figures 1 and 1A.
  • the figures show, in a sectional view, the impeller 1 and the diffuser 3 of the compressor.
  • the impeller 1 rotates about an axis R, and comprises an impeller wheel 5 with a number of impeller vanes 7 located thereon.
  • the diffuser 3 is located downstream of the impeller 1, and comprises a diffuser housing 9 with a diffuser wall 11.
  • Diffuser vanes 13 extend in the diffuser section 15 between the diffuser housing 9 and the diffuser wall 11.
  • the diffuser leads into a discharge channel 17 leading the compressed fluid away from the diffuser.
  • the compressor is, in the present embodiment, part of a turbocharger, for example for a diesel engine. It may, however, also be used in connection with other kinds of internal combustion engine. Moreover, the compressor can be used in pumps and various gas compression applications. In those cases the compressor is usually driven by an electrical motor.
  • the impeller 1 In use, the impeller 1 is driven by a turbine stage which is itself rotated by the engine exhaust gas and mechanically connected to the impeller 1. Due to this rotation, a compressible fluid (for example air) is compressed by the impeller vanes 7 and guided towards the diffuser 3. After flowing through the diffuser section 15 with the diffuser vanes 13, the compressed fluid is discharged to the discharge channel 17.
  • a compressible fluid for example air
  • the diffuser vanes 13 comprise a region 19 which is cut back in the flow direction F.
  • the cut back region 19 is, in the present embodiment, formed by inclining the vane's leading edge with respect to the flow direction F, the angle ⁇ of which is not greater than 65 degrees.
  • the flow characteristics at the leading edge 21 can be improved.
  • flow separation of the fluid 3 at the leading edge 21 can be overcome. By overcoming this flow separation, less turbulence is created and, as a consequence, the loss of efficiency in the compressor can be reduced, and its operating range increased with respect to compressors having conventional diffuser vanes.
  • FIG. 6 shows the conventional diffuser vanes
  • Figure 7 shows vanes according to the first embodiment of the invention.
  • the conventional diffuser vanes are prone to turbulence due to flow separation at their leading edges, indicated by reference numerals 23 and 25.
  • no flow separation is found on the inventive diffuser vanes, as shown in Figure 7.
  • the relationship between the pressure recovery in the diffuser and the inclination angle ⁇ of the leading edge of the diffuser vanes of the invention is depicted in Figure 5 for the first embodiment.
  • the pressure recovery is lowest for an inclination angle of 90 degrees, that is when the leading edge 21 extends perpendicular to the flow direction F.
  • the pressure recovery increases strongly with lower inclination angles, and comes very close to an asymptotic value for angles of 65 degrees or lower. In other words, if the inclination angle is 65 degrees or lower, a pressure recovery close to the maximum possible can be achieved with the invented compressor diffuser.
  • FIG. 8 The performance benefits of a compressor which uses the inclined diffuser vanes according to the first embodiment are shown in Figure 8.
  • the figure shows, as a function of the swallowing capacity of the compressor, the achievable pressure ratio and the efficiency of the compressor stage for a range of rotational speeds of the impeller.
  • the stage efficiency and operating range are higher for the current invention than with conventional diffuser vanes.
  • FIG. 2 and 2A A second embodiment of the invention is shown in Figures 2 and 2A.
  • This embodiment differs from the first embodiment in that the leading edge 121 of the diffuser vane 113 follows a curved line rather than a straight line.
  • the curvature is such that the leading edge 121 forms a cut back region.
  • the inclination angle between local line elements and the flow direction F varies.
  • the leading edge 121 comprises a region 123 in which the inclination angle is relatively low. It further comprises a region 125 in which the inclination angle is relatively high, and may reach 90 degrees at the diffuser wall 11.
  • the inclination angle ⁇ is lower than 65 degrees and increases only slowly. This low inclination angle and the fact that it increases only slowly along the leading edge 121 is sufficient to prevent flow separation.
  • a third embodiment of the invention is shown in Figures 3 and 3A.
  • the diffuser leading edge 221 is curved in such a way that its inclination angle in the region of the diffuser housing 223 is the same as that for the second embodiment shown in Figures 2 and 2A.
  • the leading edge region 225 is inclined in the opposite direction, as shown in the figures.
  • FIG. 4A A fourth embodiment of the invention is shown in Figures 4 and 4A.
  • the leading edge 321 is similar to that depicted in Figures 3 and 3A, except it is formed from two straight line regions 323 and 325, in the form of a dovetail.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP06013164A 2006-06-26 2006-06-26 Abgasturbolader mit einem Radialverdichter Withdrawn EP1873402A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06013164A EP1873402A1 (de) 2006-06-26 2006-06-26 Abgasturbolader mit einem Radialverdichter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06013164A EP1873402A1 (de) 2006-06-26 2006-06-26 Abgasturbolader mit einem Radialverdichter

Publications (1)

Publication Number Publication Date
EP1873402A1 true EP1873402A1 (de) 2008-01-02

Family

ID=37603205

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06013164A Withdrawn EP1873402A1 (de) 2006-06-26 2006-06-26 Abgasturbolader mit einem Radialverdichter

Country Status (1)

Country Link
EP (1) EP1873402A1 (de)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011011335A1 (en) * 2009-07-19 2011-01-27 Cameron International Corporation Centrifugal compressor diffuser
CN103314218A (zh) * 2010-12-10 2013-09-18 株式会社日立制作所 离心型涡轮机械
US8602728B2 (en) 2010-02-05 2013-12-10 Cameron International Corporation Centrifugal compressor diffuser vanelet
US20140112764A1 (en) * 2011-05-26 2014-04-24 Isao Morita Nozzle blade
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
KR20180019416A (ko) * 2016-08-16 2018-02-26 한화파워시스템 주식회사 원심 압축기
CN110582649A (zh) * 2017-04-07 2019-12-17 赛峰飞机发动机公司 加强的轴向扩压器
IT201900006674A1 (it) * 2019-05-09 2020-11-09 Nuovo Pignone Tecnologie Srl Paletta statorica per un compressore centrifugo
EP3760871A1 (de) * 2019-07-04 2021-01-06 Siemens Aktiengesellschaft Diffusor für eine strömungsmaschine
RU202474U1 (ru) * 2019-12-28 2021-02-19 федеральное государственное автономное образовательное учреждение высшего образования "Санкт-Петербургский политехнический университет Петра Великого" (ФГАОУ ВО "СПбПУ") Трубчатый диффузор центробежного компрессора
EP3805572A1 (de) * 2019-10-07 2021-04-14 Siemens Aktiengesellschaft Diffusor, radialturboverdichter
CN113074142A (zh) * 2020-01-06 2021-07-06 广东威灵电机制造有限公司 扩压装置、风机及吸尘器
RU2785571C1 (ru) * 2019-05-09 2022-12-08 НУОВО ПИНЬОНЕ ТЕКНОЛОДЖИ - С.р.л. Лопатка статора для центробежного компрессора

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2967013A (en) * 1954-10-18 1961-01-03 Garrett Corp Diffuser
US3963369A (en) * 1974-12-16 1976-06-15 Avco Corporation Diffuser including movable vanes
US4349314A (en) * 1980-05-19 1982-09-14 The Garrett Corporation Compressor diffuser and method
GB2237071A (en) * 1989-10-18 1991-04-24 Rolls Royce Plc Compressor assembly
US5178516A (en) * 1990-10-02 1993-01-12 Hitachi, Ltd. Centrifugal compressor
US20010036404A1 (en) * 1993-10-18 2001-11-01 Yoshihiro Nagaoka Centrifugal fluid machine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2967013A (en) * 1954-10-18 1961-01-03 Garrett Corp Diffuser
US3963369A (en) * 1974-12-16 1976-06-15 Avco Corporation Diffuser including movable vanes
US4349314A (en) * 1980-05-19 1982-09-14 The Garrett Corporation Compressor diffuser and method
GB2237071A (en) * 1989-10-18 1991-04-24 Rolls Royce Plc Compressor assembly
US5178516A (en) * 1990-10-02 1993-01-12 Hitachi, Ltd. Centrifugal compressor
US20010036404A1 (en) * 1993-10-18 2001-11-01 Yoshihiro Nagaoka Centrifugal fluid machine

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2505711C2 (ru) * 2009-07-19 2014-01-27 Камерон Интернэшнл Корпорэйшн Диффузор центробежного компрессора
CN102575688A (zh) * 2009-07-19 2012-07-11 卡梅伦国际公司 离心式压缩机扩压器
EP2623795A1 (de) * 2009-07-19 2013-08-07 Cameron International Corporation Diffusor für einen Zentrifugalverdichter
EP2623794A1 (de) * 2009-07-19 2013-08-07 Cameron International Corporation Diffusor für einen Zentrifugalverdichter
WO2011011335A1 (en) * 2009-07-19 2011-01-27 Cameron International Corporation Centrifugal compressor diffuser
CN102575688B (zh) * 2009-07-19 2015-11-25 卡梅伦国际公司 离心式压缩机扩压器
US9222485B2 (en) 2009-07-19 2015-12-29 Paul C. Brown Centrifugal compressor diffuser
US8602728B2 (en) 2010-02-05 2013-12-10 Cameron International Corporation Centrifugal compressor diffuser vanelet
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
CN103314218A (zh) * 2010-12-10 2013-09-18 株式会社日立制作所 离心型涡轮机械
CN103314218B (zh) * 2010-12-10 2016-03-09 株式会社日立制作所 离心型涡轮机械
US20140112764A1 (en) * 2011-05-26 2014-04-24 Isao Morita Nozzle blade
US9528386B2 (en) * 2011-05-26 2016-12-27 Ihi Corporation Nozzle blade
CN107762985A (zh) * 2016-08-16 2018-03-06 韩华泰科株式会社 离心式压缩机
CN107762985B (zh) * 2016-08-16 2021-01-05 韩华压缩机株式会社 离心式压缩机
KR20180019416A (ko) * 2016-08-16 2018-02-26 한화파워시스템 주식회사 원심 압축기
CN110582649A (zh) * 2017-04-07 2019-12-17 赛峰飞机发动机公司 加强的轴向扩压器
CN110582649B (zh) * 2017-04-07 2021-08-17 赛峰飞机发动机公司 加强的轴向扩压器
US20220299044A1 (en) * 2019-05-09 2022-09-22 Nuovo Pignone Tecnologie - S.R.L. Stator blade for a centrifugal compressor
WO2020224807A1 (en) * 2019-05-09 2020-11-12 Nuovo Pignone Tecnologie - S.R.L. Stator blade for a centrifugal compressor
CN113906222A (zh) * 2019-05-09 2022-01-07 诺沃皮尼奥内技术股份有限公司 用于离心式压缩机的定子叶片
IT201900006674A1 (it) * 2019-05-09 2020-11-09 Nuovo Pignone Tecnologie Srl Paletta statorica per un compressore centrifugo
RU2785571C1 (ru) * 2019-05-09 2022-12-08 НУОВО ПИНЬОНЕ ТЕКНОЛОДЖИ - С.р.л. Лопатка статора для центробежного компрессора
AU2020268493B2 (en) * 2019-05-09 2023-12-21 Nuovo Pignone Tecnologie - S.R.L. Stator blade for a centrifugal compressor
US11965527B2 (en) * 2019-05-09 2024-04-23 Nuovo Pignone Technologie Srl Stator blade for a centrifugal compressor
EP3760871A1 (de) * 2019-07-04 2021-01-06 Siemens Aktiengesellschaft Diffusor für eine strömungsmaschine
WO2021001106A1 (de) * 2019-07-04 2021-01-07 Siemens Energy Global GmbH & Co. KG Diffusor für eine strömungsmaschine
EP3805572A1 (de) * 2019-10-07 2021-04-14 Siemens Aktiengesellschaft Diffusor, radialturboverdichter
RU202474U1 (ru) * 2019-12-28 2021-02-19 федеральное государственное автономное образовательное учреждение высшего образования "Санкт-Петербургский политехнический университет Петра Великого" (ФГАОУ ВО "СПбПУ") Трубчатый диффузор центробежного компрессора
CN113074142A (zh) * 2020-01-06 2021-07-06 广东威灵电机制造有限公司 扩压装置、风机及吸尘器

Similar Documents

Publication Publication Date Title
EP1873402A1 (de) Abgasturbolader mit einem Radialverdichter
KR101178213B1 (ko) 압축기
US5554000A (en) Blade profile for axial flow compressor
WO2008035465A1 (fr) Compresseur centrifuge
US7771170B2 (en) Turbine wheel
US6234749B1 (en) Centrifugal compressor
EP1128070A2 (de) Verdichter
EP1553304A3 (de) Kreiselverdichter
EP2096264A3 (de) Turbine mit variabler Geometrie und Turbolader
US8864454B2 (en) System and method of assembling a supersonic compressor system including a supersonic compressor rotor and a compressor assembly
JP2008075536A5 (de)
WO2015099199A1 (ja) タービン
EP2535598A1 (de) Zentrifugalverdichter mit einer asymmetrischen selbst-rückzirkulierenden gehäusebearbeitung
US6796771B2 (en) Axial-flow fan
WO2017120031A1 (en) Turbocharger compressor and method
EP2423511B1 (de) Überschallverdichterrotor und Verfahren zu seiner Montage
EP3336362A1 (de) Zentrifugalverdichter und turbolader
WO2018155546A1 (ja) 遠心圧縮機
US6910861B2 (en) Turbomolecular vacuum pump with the rotor and stator vanes
EP1693574A1 (de) Laufrad von halbaxialverdichter
EP2053250A3 (de) Turbomolekularpumpe
CN110234888B (zh) 压缩机的涡旋形状以及增压器
CN108431385B (zh) 涡轮增压器压缩机和方法
US20140271173A1 (en) Centrifugal compressor with axial impeller exit
CN108474257B (zh) 涡轮增压器压缩机和方法

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

17P Request for examination filed

Effective date: 20080630

17Q First examination report despatched

Effective date: 20080814

AKX Designation fees paid

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: NAPIER TURBOCHARGERS LIMITED

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20081230