EP4215759A1 - Diffuseur pour un turbocompresseur radial - Google Patents

Diffuseur pour un turbocompresseur radial Download PDF

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Publication number
EP4215759A1
EP4215759A1 EP22153077.7A EP22153077A EP4215759A1 EP 4215759 A1 EP4215759 A1 EP 4215759A1 EP 22153077 A EP22153077 A EP 22153077A EP 4215759 A1 EP4215759 A1 EP 4215759A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
vane
along
guide vanes
flow
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Withdrawn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
EP22153077.7A
Other languages
German (de)
English (en)
Inventor
Jörg Paul HARTMANN
Michael Wannek
Attilla Yildiz
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.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
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 Energy Global GmbH and Co KG filed Critical Siemens Energy Global GmbH and Co KG
Priority to EP22153077.7A priority Critical patent/EP4215759A1/fr
Publication of EP4215759A1 publication Critical patent/EP4215759A1/fr
Withdrawn legal-status Critical Current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
    • 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

  • the invention relates to a diffuser for a radial turbocompressor, the diffuser extending annularly around a central axis, the diffuser having an inflow which is formed along at least a first section of the flow for an at least largely radial flow by means of a process fluid during operation, the diffuser having standing first guide vanes which divide the diffuser into individual circumferential segments at least along a radial section, the first guide vanes dividing in the direction of the flow from a first leading edge to a first trailing edge along a first chord length S1, with the diffuser having stationary second guide vanes which divide the diffuser into individual circumferential segments at least along a radial section, with the second guide vanes extending in the direction of flow from a second leading edge to a second trailing edge along a second chord length S2, with the diffuser having a first diffuser boundary contour in the region of the first section on a first axial side and has a second diffuser delimitation contour on a second axial side, wherein the first
  • the fluid leaves the impeller radially outwards and from there reaches the diffuser, which is typically also flown through radially from the inside outwards.
  • the diffuser according to the invention is designed with blades. With regard to the blading, a distinction is made between low-solidity diffusers [LSD] with low blade overlap (with vanes, which have a relatively large distance from each other in the circumferential direction in relation to their radial extension) and channel diffusers - also referred to as aerodynamic diffusers [AE diffusers] - distinguished.
  • ribbed guide vanes and guide vanes which - unlike the ribbed guide vanes - extend over the entire axial duct height of the diffuser, with the ribbed guide vanes being located upstream of the other guide vanes, it is disadvantageous that the ribbed guide vanes can trigger detachment phenomena in the throughflow in the area of their axial termination in the flow duct.
  • the ribbed guide vanes can cause a dead water region downstream that extends over part of the channel height, so that from an axial perspective, the flow pattern through the diffuser can also become less uniform through the use of ribbed guide vanes, so that positive effects in aerodynamic terms are at least partially canceled out again.
  • the invention has set itself the task of providing a more uniform flow control.
  • radial, axial, tangential or circumferential refer to the initially defined axis around which the diffuser extends annularly. In the case of a turbo compressor or a radial turbo compressor, this axis is coaxial to the axis of rotation of the rotor.
  • the invention understands a profile center line to be an imaginary line that extends through the center of a blade profile.
  • the blade profile is interpreted as a two-dimensional shape.
  • the profile centerline can be constructed in this two-dimensional form, for example by connecting the centers of all inscribed circles with a line - the profile centerline.
  • the diffuser is defined axially by diffuser boundary contours.
  • diffuser boundary contours is not to be understood in such a way that the diffuser boundary contours always have an axial surface normal. Rather, this term is intended to mean that the diffuser boundary contours in any case have a radial extension and—even if they have a course that is inclined relative to the radial or axial—bound the diffuser in the axial direction.
  • a further advantageous development of the invention provides that the axial distance between diffuser boundary contours widens in the radial direction.
  • the diffuser is a flow-guiding component of the stator, which is located downstream of the impeller outlet.
  • the flow speed of the process fluid is generally delayed in the diffuser, so that a pressure build-up results according to Bernoulli's laws.
  • the diffuser effect results simply from the radial increase in the cross-sectional area through which flow occurs.
  • a change in the diffuser channel width which usually results from the axial extension of the clear width of the diffuser, is also of importance.
  • the diffuser can also extend in a manner deviating from the radial direction. Most diffusers extend largely radially.
  • the diffuser channel width is limited by provided on both sides diffuser boundary contours. In the case of a purely radially extending diffuser without axial widening, the diffuser boundary contours also run purely radially.
  • the impeller is usually constructed with a wheel disk that connects the impeller to the shaft with a shaft-hub connection.
  • the side that does not have the axial suction of the impeller is referred to as the hub side.
  • the other opposite axial side is referred to as the housing side.
  • this side of the housing is also often referred to as the cover plate side.
  • the invention understands a blade height to be the extent of the blade perpendicular to the main direction of flow. If one follows a flow thread—representative of the main flow direction—through the arrangement of the invention, for example through the diffuser, then this flow thread extends essentially perpendicularly to the direction of the blade height. If this streamline extends approximately in the middle of the arrangement, it will be at approximately 50% of the blade height.
  • stationary guide vanes to mean guide vanes which are firmly connected to the stator and cannot be moved relative to the rest of the stator in order to change the aerodynamic conditions during operation.
  • These guide vanes divide the diffuser into individual circumferential segments at least along a radial section. As a rule, such a division does not take place strictly by means of guide vanes running purely radially, but rather by means of guide vanes extending obliquely to the radial. In the area of the curved entry edge, such a segmentation is not given over the entire axial channel width. However, the invention provides that at least radially in sections Guide vanes extend over the entire width of the channel, thereby separating circumferential segments from one another.
  • the peripheral segments of claim 1 or the set of patent claims are conceptually synonymous with flow channels between the guide vanes of the diffuser, which extend essentially from radially inside to radially outside or are flown through along this direction.
  • chord length is the length of the profile chord - i.e. an imaginary connecting line between the profile nose and the profile trailing edge or the leading edge of the guide vane and the trailing edge.
  • blading is used in the radial diffuser, which, in addition to advantages, all have specific disadvantages.
  • blading has been used which uses the full channel width of the radial diffuser over the entire blade length (full blade) or only a small part (RIB diffusers).
  • the present proposal solves this problem by combining the advantages of both variants and minimizing the disadvantages.
  • the figure 1 shows a schematic longitudinal section along an axis of rotation 2 through a radial turbocompressor 1 with a diffuser 3 according to the invention.
  • figure 1 shows a centrifugal turbocompressor 1 with a diffuser 3 and an impeller 4 arranged upstream of the diffuser 3.
  • the impeller 4 and the diffuser 3 extend annularly along a circumferential direction 5 of an axis X with an axis of rotation 2.
  • the impeller 4 is fixed in a specific axial position on a shaft 6 rotatably mounted about the axis of rotation 2 or the axis X, which is arranged coaxially with the axis of rotation ROT.
  • the impeller 4 has a wheel disk 7 , impeller blades 8 and a cover disk 9 , the impeller blades 8 forming flow channels being fastened between the wheel disk 7 and the cover disk 9 .
  • a process fluid is sucked in axially and deflected outwards in the radial direction, where it exits the rotating impeller 4 during operation and reaches a static diffuser 3 .
  • the process fluid flows from the diffuser 3 into a collecting spiral 10 . From there, the process fluid is fed from the radial turbocompressor 1 to units located downstream in a manner that is not shown.
  • the figure 2 shows a schematic perspective view of a part of the diffuser 3 according to the invention.
  • the diffuser 3 comprises a plurality of guide vanes 11 distributed in the circumferential direction. These guide vanes 11 are distributed at equidistant intervals around the circumference.
  • the guide vane 11 comprises a first guide vane 12 and a second guide vane 13 . This will be in the figure 3 explained in more detail.
  • the diffuser 3 extends annularly around a central axis 2 and has an inflow which is formed along at least a first section of the flow for an at least largely radial flow by means of a process fluid during operation.
  • the diffuser 3 has standing first guide vanes 11 which divide the diffuser 3 into individual circumferential segments at least along a radial section.
  • the first guide vane 11 extends in the direction of flow from a first leading edge 14 to a first trailing edge 15 along a first chord length S1.
  • the diffuser 3 has standing second guide vanes 13 which divide the diffuser 3 into individual circumferential segments at least along a radial section.
  • the second guide vane 13 extends in the direction of flow from a second leading edge 16 to a second trailing edge 17 along a first chord length S2.
  • the diffuser 3 has a first diffuser boundary contour on a first axial side and a second diffuser boundary contour on a second axial side, with the first guide vanes 12 and second guide vanes 13 at least along part extending in the direction of flow transversely thereto from the first diffuser boundary contour to the second diffuser boundary contour along a blade height, the first guide vane 12 having a first vane height H1, the second guide vane 13 having a second vane height H2.
  • the second vane 13 is disposed on the first vane 12 along the vane height H2 with the second chord length S2 being shorter than the first chord length S1.
  • H1 a*H2, where a has a value between 0.1 and 0.5, in particular a value between 0.2 and 0.4 and very particularly a value between 0.25 and 0.35.
  • the first leading edge 14 of the first guide vane 12 and the second leading edge 16 of the second guide vane 13 are formed essentially parallel to one another.
  • first trailing edge 15 of the first vane 12 and the second trailing edge 17 of the second vane 13 form a common axis. This means that the trailing edges of the first guide vane 12 and the second guide vane 13 are essentially identical to one another.
  • FIG. 4 shows a plan view of the first guide vane 12 and the second guide vane 13, the second guide vane 13 being arranged on the first guide vane 12.
  • the first guide blade 12 has a first profiling 18 .
  • the second vane 13 has a second profiling 19 .
  • the first profiling 18 is essentially identical to the second profiling 19, with the second profiling 19 being scaled compared to the first profiling.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP22153077.7A 2022-01-25 2022-01-25 Diffuseur pour un turbocompresseur radial Withdrawn EP4215759A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP22153077.7A EP4215759A1 (fr) 2022-01-25 2022-01-25 Diffuseur pour un turbocompresseur radial

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP22153077.7A EP4215759A1 (fr) 2022-01-25 2022-01-25 Diffuseur pour un turbocompresseur radial

Publications (1)

Publication Number Publication Date
EP4215759A1 true EP4215759A1 (fr) 2023-07-26

Family

ID=80034749

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22153077.7A Withdrawn EP4215759A1 (fr) 2022-01-25 2022-01-25 Diffuseur pour un turbocompresseur radial

Country Status (1)

Country Link
EP (1) EP4215759A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03134298A (ja) * 1989-10-20 1991-06-07 Hitachi Ltd 遠心圧縮機の羽根付デイフユーザ
DE69434033T2 (de) * 1993-10-18 2005-09-22 Hitachi, Ltd. Kreiselaggregat für Fluide
EP1860325A1 (fr) * 2006-05-26 2007-11-28 ABB Turbo Systems AG Diffuseur
JP2016176399A (ja) * 2015-03-19 2016-10-06 三菱重工業株式会社 ディフューザ、及び、遠心式流体機械
CN107676305A (zh) * 2017-08-10 2018-02-09 中国北方发动机研究所(天津) 一种阶梯型导流叶片有叶扩压器结构

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03134298A (ja) * 1989-10-20 1991-06-07 Hitachi Ltd 遠心圧縮機の羽根付デイフユーザ
DE69434033T2 (de) * 1993-10-18 2005-09-22 Hitachi, Ltd. Kreiselaggregat für Fluide
EP1860325A1 (fr) * 2006-05-26 2007-11-28 ABB Turbo Systems AG Diffuseur
JP2016176399A (ja) * 2015-03-19 2016-10-06 三菱重工業株式会社 ディフューザ、及び、遠心式流体機械
CN107676305A (zh) * 2017-08-10 2018-02-09 中国北方发动机研究所(天津) 一种阶梯型导流叶片有叶扩压器结构

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