EP3760876A1 - Diffuseur pour une turbomachine - Google Patents

Diffuseur pour une turbomachine Download PDF

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Publication number
EP3760876A1
EP3760876A1 EP19184292.1A EP19184292A EP3760876A1 EP 3760876 A1 EP3760876 A1 EP 3760876A1 EP 19184292 A EP19184292 A EP 19184292A EP 3760876 A1 EP3760876 A1 EP 3760876A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
rib
guide vanes
arrangement
rpv
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Withdrawn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
EP19184292.1A
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German (de)
English (en)
Inventor
Nico Petry
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 AG
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 EP19184292.1A priority Critical patent/EP3760876A1/fr
Publication of EP3760876A1 publication Critical patent/EP3760876A1/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Withdrawn legal-status Critical Current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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F05D2220/3217—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the first stage of a compressor or a low pressure compressor
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to an arrangement with a diffuser for a turbomachine with an impeller upstream of the diffuser, the diffuser and the impeller extending annularly around an axis along a circumferential direction, the ribbed guide vanes extending along the vane height between two diffuser boundary walls starting from a diffuser boundary wall on one Housing side extending in the direction of a diffuser boundary wall on a hub side, the rib guide vanes extending from the housing side along 25% -50% of the diffuser channel width in the direction of the hub side, the rib guide vanes having leading edges which are arranged on a mean rib leading edge diameter, the impeller having impeller blades wherein the impeller blades have rotor trailing edges, the rotor trailing edges being arranged on a mean rotor trailing edge diameter over the respective blade height.
  • the invention also relates to a turbomachine with such an arrangement.
  • the fluid leaves the impeller radially outwards and from there reaches the diffuser, which typically also has a radial flow from the inside to the outside.
  • Diffusers can be bladed or bladed.
  • LSD low solidity diffusers
  • AE diffuser aerodynamic diffusers
  • LSDs offer a significantly better and more extensive driving range than AE diffusers. Almost all bladed diffusers today are LSDs.
  • Diffusers for radial machines are already from the EP 2 650 546 A1 known. It is proposed there to arrange the guide vanes of the diffuser in an inclined shape in a standing diffuser arranged behind the impeller (dihedral vanes). With the LSD in particular, this aerodynamic measure is intended to achieve a reduced pressure loss.
  • the main task of the invention is to reduce the radial installation space requirement of an LSD so that the otherwise increased radial installation space requirement is no longer so significant compared to an unbladed diffuser.
  • radial, axial, tangential or circumferential direction relate to the axis defined at the outset, around which the diffuser extends in an annular manner. In the case of a turbo compressor or a radial turbo compressor, this axis is coaxial with the axis of rotation of the rotor.
  • circumferential tangent in the present case also denoted by the reference symbol CDT always means a tangent that touches a circular line around the central axis, the circle radius and the point of contact each clearly arising from the context for the person skilled in the art.
  • 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 understood as a two-dimensional shape.
  • the profile center line can be constructed in this two-dimensional form, for example by connecting the centers of all inscribed circles by means of a line - the profile center line.
  • the diffuser is defined axially by diffuser boundary walls.
  • diffuser boundary walls is not to be understood in such a way that the diffuser boundary walls always have an axial surface normal. Rather, this term is intended to mean that the diffuser boundary walls in any case have a radial extent and - even if they have an oblique course with respect to the radial or axial direction - limit the diffuser in the axial direction.
  • Another advantageous development of the invention provides that the axial distance between diffuser boundary walls widens in the radial direction.
  • turbomachine relates to radial turbomachines which provide a deflection of the process fluid.
  • the application for a radial turbo compressor is of primary importance.
  • the diffuser is a flow-guiding component of the stator, which is located downstream of the impeller outlet.
  • the flow rate of the process fluid is delayed in the diffuser, so that a pressure build-up results in accordance with Bernoulli's principles.
  • the diffuser effect results from the radial increase in the cross-sectional area through which the flow passes.
  • a change in the diffuser channel width which usually results from the axial extension of the clear width of the diffuser.
  • the diffuser can also extend in a manner deviating from the radial direction. Most diffusers, however, extend largely radially.
  • the diffuser channel width is limited by the diffuser boundary walls provided on both sides. In the case of a purely radially extending diffuser without axial widening, the diffuser boundary walls also run purely radially.
  • the impeller Due to the axial intake of a radial turbo compressor and the radial output of the process fluid from the impeller, in the impeller is deflected from axially to radially.
  • the impeller is usually constructed with a wheel disc which 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 here as the hub side.
  • the other opposite axial side is referred to as the housing side.
  • this housing side is also often referred to as the cover disk side.
  • the invention understands a blade height as the extension of the blade perpendicular to the main flow direction.
  • this flow thread extends essentially perpendicular to the direction of the blade height. If this flow thread extends approximately centrally through the arrangement, it will be approximately 50% of the blade height.
  • a rib entry angle REA is defined with respect to the entry edge angle of the diffuser guide vanes and is preferably between 14 ° and 22 °. This geometry effectively takes into account the peculiarities of the ribbed vanes and the flow technology downstream of the impeller.
  • the rib angle difference between the rib entry angle and rib exit angle is designed as a metal angle between 4 ° and + 11 °, preferably between 6 ° to 10 °.
  • the fin guide vanes have a vane overlap for each position of the vane height, which is defined as the ratio of a chord length of the respective fin guide vane to the circumferential pitch of the arrangement of the fin guide vanes.
  • the invention understands the profile chord to be the imaginary connecting line between the leading edge of the profile and the trailing edge or trailing edge.
  • the circumferential division - also often referred to simply as a division - is understood to mean the distance in the circumferential direction between the leading edges of the fin guide vanes.
  • An advantageous development of the invention in this regard provides that the mean blade overlap (SLD) of the rib guide vanes is between 0.6 ⁇ SLD ⁇ 0.9, preferably between 0.65 ⁇ SLD ⁇ 0.75.
  • the impeller has an axial impeller outlet width at the outlet, the diffuser having an axial diffuser duct inlet width at the inlet, an annular space width ratio being defined as the axial diffuser duct inlet width to the axial impeller outlet width, the annular space width ratio ACW preferably 0.8 ⁇ ACW ⁇ 1, particularly preferably between 0.85 ⁇ ACW ⁇ 0.98.
  • This ratio leads to surprisingly good aerodynamic results with reduced radial space requirements.
  • the diffuser has, downstream of the ribbed guide vanes, diffuser guide vanes which, starting from the housing side, extend along the diffuser channel width to the hub side.
  • the diffuser guide vanes are arranged downstream of the rib guide vanes for at least 70% of their chord lengths.
  • the ribbed guide vanes also take into account the fact that the process fluid emerging from the impeller has a different flow distribution and speed distribution on the housing side has than on the hub side. To compensate for this difference, the ribbed guide vanes are provided in front of the actual diffuser guide vanes, so that these differences are better compensated and the most homogeneous outflow possible takes place behind the outlet of the diffuser.
  • the invention proposes as an advantageous development that the ribbed guide vanes and / or the diffuser guide vanes have a curved and profiled profile.
  • Profiled means that the blade profile does not have a constant thickness over the extent in the main flow direction, but is aerodynamically adapted with regard to the profile thickness distribution.
  • the blade or the blade profile on the pressure side is designed to be more concave over a wider area than on the suction side - accordingly, the blade profile on the suction side is designed to be convex over a further area of extent.
  • an angle of attack is defined as the mathematically positive angle from the circumferential tangent to the tangent at the profile center line.
  • a leading edge angle is an angle of attack at the leading edge and an exit edge angle is an angle of attack at the trailing edge of the diffuser guide vane.
  • leading edge angle is between 23 ° ⁇ LEA ⁇ 30 ° ..
  • leading edge angle For the difference between the leading edge angle and the trailing edge angle averaged over the blade height, the following preferably applies: -4> leading edge angle - trailing edge angle> 10 °.
  • a negative difference between the leading edge angle and the exit angle or the rib entry angle and the rib exit angle indicates that the blade tapers more tangentially than the inlet is designed.
  • a flow fluid that would at least largely or completely follow such a blade design has a more tangential flow orientation after flowing through such a blade arrangement with such a negative difference.
  • ratio of the number of rib guide vanes to the number of diffuser guide vanes is 0.5, 1 or 2. It is useful if the arrangement has 8-24 diffuser guide vanes.
  • the diffuser in the area of the inlet edges of the diffuser guide vanes the diffuser has an axial diffuser guide vane inlet width, with the diffuser having an axial diffuser guide vane outlet width in the area of the outlet edges of the diffuser guide vanes, a guide vane inlet guide vane outlet width being defined as the axial diffuser guide vane width ratio to the diffuser guide vane outlet width 1 , 0 ⁇ AVW ⁇ 1 , 4th
  • the diffuser boundary wall on the hub side extends less obliquely to the radial direction than the diffuser boundary wall on the housing side, such that at least 80% of the axial expansion results from the inclination of the diffuser boundary wall on the housing side.
  • the invention also relates to a turbomachine with an arrangement of the type defined above.
  • Figure 1 shows a fluid flow machine CMP with an arrangement ARA with a diffuser DFF and an impeller IMP arranged upstream of the diffuser DFF.
  • the impeller IMP and the diffuser DFF extend annularly along a circumferential direction CDR of an axis X with an axis of rotation ROT.
  • the impeller IMP is fastened in a specific axial position to a shaft SHT which is rotatably mounted about the axis of rotation ROT or the axis X arranged coaxially to the axis of rotation ROT.
  • the impeller IMP has a wheel disc HUB, impeller blades BLD and a cover plate SHR, the impeller blades BLD being attached between the wheel disc HUB and the cover plate SHR, forming flow channels.
  • a process fluid PFL is sucked in axially and deflected outward in the radial direction, where it exits the rotating impeller IMP during operation and enters a static diffuser DFF.
  • Ribbed guide vanes RPV of the static diffuser DFF homogenize and correct the speed distribution of the exiting process fluid PFL before it is introduced into a spiral VLT.
  • the rib guide vanes RPV extend along the vane height AFH between two diffuser boundary walls LDW starting from a diffuser boundary wall LDW on a housing side CSS in the direction of a diffuser boundary wall LDW on a hub side HBS.
  • the impeller IMP has an axial impeller outlet width AXW at the outlet, the diffuser DFF having an axial diffuser channel inlet width IDW at the inlet, an annular space width ratio ACW being defined as the axial diffuser channel inlet width IDW to the axial impeller outlet width (AXW): 0.8 ⁇ ACW ⁇ 1, the following applies particularly preferably: 0 , 85 ⁇ ACW ⁇ 0 , 98
  • FIG Figure 2 shows a section according to II-II of FIG Figure 1 schematic.
  • the impeller IMP is shown rotatable about the X axis.
  • the impeller blades BLD of the impeller IMP are shown schematically with a concave pressure side PRS and a convex suction side SCS - as are the ribbed guide vanes RPV.
  • the rotor trailing edges RRE of the impeller blades BLD are set back somewhat compared to the maximum diameter IPD of the impeller IMP on a rotor trailing edge diameter TRI. Downstream there are leading edges LEE of the fin guide vanes RPV on a leading edge diameter DLE.
  • Figure 3 shows a detail that is in the Figure 2 is shown with III.
  • the ones in the Figure 3 The illustrated relationships relate to angular relationships on ribbed guide vanes RPV and also to diffuser guide vanes VNS, which with the respective blade height AFH not only extend over part of the diffuser channel width ADW, but over the entire axial distance of the diffuser boundary walls LDW.
  • the relationships shown in this presentation apply mutatis mutandis to diffuser guide vanes VNS or ribbed guide vanes RPV, so that in FIG Figure 3 partly also identical reference symbols - which indicate an identical component meaning - and relationships are reproduced for both arrangements.
  • the two in Figure 3 illustrated exemplary ribbed guide vanes RPV or diffuser guide vanes VNS (hereinafter referred to as Figure 3 only referred to as diffuser guide vanes VNS) have for each position of the vane height AFH in their arrangement to each other a vane overlap SLD, which is defined as the ratio of a chord length CHD of the respective diffuser vane VNS to the circumferential pitch CCP of the arrangement of the ribbed vanes RPV or diffuser vanes VNS.
  • the mean blade overlap SLD of the ribbed guide vanes RPV is between 0.6 ⁇ SLD ⁇ 0.9, particularly preferably 0.65 ⁇ SLD ⁇ 0.75.
  • an angle of attack PMA is defined as the mathematically positive angle from the circumferential rod CDT to the tangent PMT at the profile center line SCL of the profile.
  • a leading edge angle LEA or rib entry angle REA is an angle of attack PMA at the leading edge LEE of a diffuser guide vane VNS or rib guide vane RPV.
  • An exit edge angle EXA is an angle of attack PMA at an exit edge TRE of the diffuser guide vanes VNS.
  • a rib entry angle REA is a rib angle of attack RMA at an entry edge LEE of a rib guide vane RPV, where the following applies to the mean rib entry angle REA: 12 ° ⁇ REA ⁇ 20th ° .
  • the rib guide vanes RPV 4th ° ⁇ REA - RXA ⁇ 11 ° , prefers 6th ° ⁇ REA - RX ⁇ 10 ° .
  • FIG. 4 and 5 also the Figure 6 show different views of an embodiment with diffuser guide vanes VNS arranged downstream of the ribbed guide vanes RPV, which, starting from the housing side CSS, extend along the entire diffuser channel width ADW in the direction of the hub side HBS.
  • the leading edge angle LEA of the diffuser guide vanes VNS is between 23 ° ⁇ LEA ⁇ 30 °, whereby the following preferably applies for a difference leading edge angle (LEA) - exit edge angle (EXA) for the diffuser guide vanes VNS: - 4th ° ⁇ LEA - EXA ⁇ 10 ° .
  • a diffuser guide vane VNS is arranged upstream of the rib guide vane RPV, the following preferably applies: 12 ° > REA > 20th ° .
  • the ratio of the number of rib guide vanes RPV to the number of diffuser guide vanes VNS is particularly expediently: 0.5 or 1 or 2.
  • the arrangement ARA has 8-24 diffuser guide vanes VNS particularly expediently.
  • a blade overlap SLD between 0.45 and 0.9, particularly preferably between 0.65 and 0.75, applies.
  • the blade overlap SLD is defined here as the ratio of a profile chord length CHD of the respective diffuser blade VNS to the circumferential pitch CCP of the arrangement of the diffuser blades VNS.
  • Figure 6 shows the combination of the axial expansion of the diffuser channel width or the inclined housing-side diffuser boundary wall LDW with the arrangement of the ribbed guide vanes RPV upstream of the diffuser guide vanes VNS. Furthermore shows Figure 6 an expansion of the axial distance between the axial diffuser boundary walls LDW with increasing radial extent.
  • the diffuser boundary walls LDW are designed in such a way that the diffuser boundary wall LDW extends less obliquely to the radial direction on the hub side HUB than the diffuser boundary wall LDW on the housing side SHR. This results in an axial expansion of at least 80% exclusively from the inclination of the diffuser boundary wall LDW on the CSS side of the housing.
  • the diffuser DFF in the area of the inlet edges LEE of the diffuser guide vanes VNS the diffuser DFF has an axial diffuser guide vane inlet width IVW, wherein in the area of the outlet edges of the diffuser guide vanes VNS the diffuser DFF has an axial diffuser guide vane outlet width AVW defined as a diffuser guide vane outlet width AVW axial diffuser guide vane outlet width EVW for axial diffuser guide vane inlet width IVW 1 , 0 ⁇ AVW ⁇ 1 , 4th
  • the leading edges LEE of the diffuser guide vanes VNS outside a surrounding area of +/- 10% of the pitch CCP of the ribbed guide vanes RPV in the circumferential direction CDR starting from a Tangent to the profile center line RHD of the rib guide vane RPV at the trailing edge TRE of the rib guide vanes RPV arranged upstream of the diffuser guide vanes VNS.
  • the number of diffuser guide vanes VNS is twice as high as that of the ribbed guide vane RPV and the diffuser guide vanes VNS are particularly preferably located, starting from a tangent to the profile center line RHD of the ribbed guide vane RPV, on the trailing edge TRE of the ribs VNS arranged upstream of the diffuser guide vanes RPV Ribbed vanes RPV.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19184292.1A 2019-07-04 2019-07-04 Diffuseur pour une turbomachine Withdrawn EP3760876A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19184292.1A EP3760876A1 (fr) 2019-07-04 2019-07-04 Diffuseur pour une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19184292.1A EP3760876A1 (fr) 2019-07-04 2019-07-04 Diffuseur pour une turbomachine

Publications (1)

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EP3760876A1 true EP3760876A1 (fr) 2021-01-06

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EP19184292.1A Withdrawn EP3760876A1 (fr) 2019-07-04 2019-07-04 Diffuseur pour une turbomachine

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113464497A (zh) * 2021-06-24 2021-10-01 珠海格力电器股份有限公司 扩压器、压缩机和空气循环机

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4850795A (en) 1988-02-08 1989-07-25 Dresser-Rand Company Diffuser having ribbed vanes followed by full vanes
EP0446900A1 (fr) 1990-03-14 1991-09-18 Hitachi, Ltd. Compresseur à écoulement mixte
US5178516A (en) * 1990-10-02 1993-01-12 Hitachi, Ltd. Centrifugal compressor
US5529457A (en) * 1994-03-18 1996-06-25 Hitachi, Ltd. Centrifugal compressor
EP1860325A1 (fr) * 2006-05-26 2007-11-28 ABB Turbo Systems AG Diffuseur
EP2650546A1 (fr) 2010-12-10 2013-10-16 Hitachi, Ltd. Turbomachine centrifuge
WO2019057413A1 (fr) 2017-09-20 2019-03-28 Siemens Aktiengesellschaft Dispositif pouvant être parcouru par un flux
WO2019057414A1 (fr) 2017-09-20 2019-03-28 Siemens Aktiengesellschaft Dispositif pouvant être parcouru par un flux
WO2019057412A1 (fr) 2017-09-20 2019-03-28 Siemens Aktiengesellschaft Dispositif pouvant être parcouru par un flux

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4850795A (en) 1988-02-08 1989-07-25 Dresser-Rand Company Diffuser having ribbed vanes followed by full vanes
EP0446900A1 (fr) 1990-03-14 1991-09-18 Hitachi, Ltd. Compresseur à écoulement mixte
US5178516A (en) * 1990-10-02 1993-01-12 Hitachi, Ltd. Centrifugal compressor
US5529457A (en) * 1994-03-18 1996-06-25 Hitachi, Ltd. Centrifugal compressor
EP1860325A1 (fr) * 2006-05-26 2007-11-28 ABB Turbo Systems AG Diffuseur
EP2650546A1 (fr) 2010-12-10 2013-10-16 Hitachi, Ltd. Turbomachine centrifuge
WO2019057413A1 (fr) 2017-09-20 2019-03-28 Siemens Aktiengesellschaft Dispositif pouvant être parcouru par un flux
WO2019057414A1 (fr) 2017-09-20 2019-03-28 Siemens Aktiengesellschaft Dispositif pouvant être parcouru par un flux
WO2019057412A1 (fr) 2017-09-20 2019-03-28 Siemens Aktiengesellschaft Dispositif pouvant être parcouru par un flux

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
SOROKES J M ET AL: "EXPERIMENTAL RESULTS ON A ROTATABLE LOW SOLIDITY VANED DIFFUSER", INTERNATIONAL GAS TURBINE AND AEROENGINE CONGRESS ANDEXPOSITION, XX, XX, 1 June 1992 (1992-06-01), pages 1 - 09, XP000565938 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113464497A (zh) * 2021-06-24 2021-10-01 珠海格力电器股份有限公司 扩压器、压缩机和空气循环机

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