EP3690254A1 - Roue à aubes d'une turbomachine radiale, turbomachine radiale - Google Patents

Roue à aubes d'une turbomachine radiale, turbomachine radiale Download PDF

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Publication number
EP3690254A1
EP3690254A1 EP19154646.4A EP19154646A EP3690254A1 EP 3690254 A1 EP3690254 A1 EP 3690254A1 EP 19154646 A EP19154646 A EP 19154646A EP 3690254 A1 EP3690254 A1 EP 3690254A1
Authority
EP
European Patent Office
Prior art keywords
blades
impeller
radial
imp
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Withdrawn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
EP19154646.4A
Other languages
German (de)
English (en)
Inventor
Jörg Paul HARTMANN
Viktor Hermes
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 EP19154646.4A priority Critical patent/EP3690254A1/fr
Publication of EP3690254A1 publication Critical patent/EP3690254A1/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Withdrawn legal-status Critical Current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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/286—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction

Definitions

  • Impellers of the type of radial turbomachinery defined at the outset basically carry out two flow-changing processes at the same time, namely a deflection from an axial flow direction into a radial flow direction - or vice versa - and an acceleration or deceleration of the process fluid.
  • the impeller as a component of a radial compressor, the statements also being valid for a radial expander reversing the statements relating to the flow, so that the alternative to the compressor of the radial turbomachine can also be subsumed under the invention and the statements made here .
  • the object of the invention is to reduce the aerodynamic loss in the impeller and behind the impeller downstream.
  • the invention proposes an impeller of the type defined at the outset with the additional features of the characterizing part of claim 1 and a radial turbine machine with such an impeller, the dependent subclaims each containing advantageous developments of the invention.
  • the outer cut (in the sense of radially outside) of the impeller blade is sometimes referred to with a cover disk, regardless of whether the impeller is designed with or without a cover disk.
  • the present invention relates to open and closed impellers alike.
  • the invention is based, among other things, on the following considerations.
  • work on the fluid is carried out in the impeller in the form of pressure change work and by supplying kinetic energy.
  • impellers are being developed that realize increasingly higher specific volume flows.
  • the inlet and outlet heights and widths - i.e. the inflow and outflow cross sections - must be increased.
  • the blade length in the direction of flow on the cover disk with closed impellers - or at the tip of the blade with open impellers - becomes increasingly shorter compared to the blade length on the wheel disk.
  • a possible countermeasure is a change of the outer lane to the inner lane such that the outer lane is again approximately the same length as the inner lane.
  • this measure inevitably leads to a longer extension in the circumferential direction - that is to say to a larger wrap angle of the outer track. Since a blade that has a larger wrap angle on the cover disk in comparison to the wheel disk in the circumferential direction is unfavorable, in particular for mechanical and manufacturing reasons, this measure has narrow limits. A large difference in the blade length on the cover and wheel disc, together with the greater curvature on the cover disc in a meridional section, means that the flow at the cover disc or blade tip is often overloaded.
  • the invention provides a remedy by means of an intermediate wall which extends in a circumferential direction and separates the flow channels - that is to say first blade channels and second blade channels.
  • the impeller is comparatively designed as a "double-decker” or even “multiple-decker” with several false ceilings.
  • cross flows to the main flow direction in the area of the intermediate wall are prevented, and on the other hand, the construction with the intermediate wall enables individual blade design and an individualized number of blades in the two planes of the impeller, which are largely parallel to one another.
  • two impeller flow passages are created, which can differ in their design and thus represent a further degree of freedom for optimizing the impeller performance.
  • the inflow cross sections and outflow cross sections of the individual blade channels can be optimized for their respective aerodynamic task.
  • the invention designates an average main flow direction of a process fluid flowing through the impeller.
  • the impeller has a cover disk extending in the circumferential direction and the second vane channels extend transversely to a second flow direction up to the cover disk.
  • the difference between a cover plate and an intermediate wall in the terminology of the invention is that there are blades on an intermediate wall radially on the outside and no blades are attached to the cover plate on the radially outside, which delimit individual blade channels for the process fluid from one another in the circumferential direction.
  • the second flow channels or second blade channels or, in the case of further blade channel levels of the impeller the outermost blade channels are designed either with or without a cover disk. If the cover plate is missing, a flow contour of the stator delimits the second blade channels radially outwards. As a result of the flow being held at the respective limiting contour, this variant represents a significantly different aerodynamic situation compared to the closed impeller.
  • the first axial flow opening has a first radial height defined by the radial blade height of the first blades (a radial compressor is the inflow into the impeller), the second axial flow opening using a the radial blade height of the second blades has a second radial height, where: 0.3 ⁇ B12 / B11 ⁇ 0.7 with B11 as the first radial height and B12 as the second radial height.
  • the following range for the ratio has proven to be particularly advantageous: 0.4 ⁇ B12 / B11 ⁇ 0.55, with B11 as the first radial height and B12 as the second radial height.
  • first blades or of the second blades are designed as splinter blades.
  • Splinter blades are blades with an axially or radially recessed leading edge (axial recess on compressors, radial recess on expanders).
  • the preferred variant of the use of splinter blades is an alternating arrangement of splitter blades and normally designed blades which have an inlet edge positioned upstream above the splitter blades.
  • a first blade thickness of the first blades averaged over the blade height and profile extension is configured differently than a second blade thickness of the second blades averaged over the blade height and profile extension.
  • a further advantageous optimization of the invention provides that the first blades have at least in part a first deflecting metal angle averaged over the blade height, the second blades at least in part having a second deflecting metal angle averaged over the blade height, the first deflecting metal angle being embodied differently from that second deflection metal angle.
  • the deflection metal angles of all first blades are particularly preferably identical.
  • the deflection metal angles of all second blades are particularly preferably identical.
  • the invention understands the respective metal angle as the angle which refers to the actual geometric conditions of the blades in question. The actual flow deflection in a circumferential direction can soften significantly from the deflection metal angle.
  • the deflection metal angle is a size averaged over the height of the bucket. If the deflection from axial to radial or vice versa is disregarded, for a middle or height-averaged blade profile it is an angle between the tangent to the chord at the leading edge to a tangent to the chord at the trailing edge.
  • FIG 1 schematically shows a radial turbomachine RTM according to the invention with a housing CAS and a rotor, which comprises a shaft SHT and an impeller IMP according to the invention.
  • Support for the shaft SHT extending along an axis X is provided by two BEA bearings.
  • the housing CAS is sealed to the environment by means of a shaft seal SHS provided in the area of the two bearings between the housing CAS and the shaft SHT.
  • the impeller IMP extends along a circumferential direction CDR about the axis X. It comprises a wheel disk HWL, a plurality of first blades BL1, a plurality of second blades BL2, a plurality of first blade channels CN1 arranged between the first blades BL1 and a plurality between the second blades BL2 arranged second blade channels CN2.
  • the first blade channels CN1 have first axial flow openings IN1 for a flow in the axial direction and first radial flow openings EX1 for a flow in the radial direction.
  • the second blade channels CN1 in turn comprise second axial flow openings IN2 for a flow in the axial direction and first radial flow openings EX2 for a flow in the radial direction.
  • the first blade channels CN1 extend along the wheel disk HWL transversely to a first flow direction FD1 along a curved flow path through the impeller IMP to an intermediate wall CVW which extends in the circumferential direction CDR.
  • the second blade channels CN2 of the impeller IMP extend in the circumferential direction CDR separated from one another by means of second blades BL2 along the intermediate wall DVW.
  • the second blade channels CN2 have second axial flow openings IN2 for a flow in the axial direction and second radial flow openings EX2 for a flow in the radial direction.
  • the Figure 1 shows an impeller IMP with a cover disk SHR, which delimits the second flow channels radially outward.
  • the omission of the cover disk SHR is conceivable in the sense of the invention, so that the first vane channels CN1 are closed vane channels and the second vane channels CN2 are open vane channels.
  • the second variant is not shown separately, but by means of Figure 1 also disclosed here, the component with the reference symbol SHR (cover plate SHR) being omitted in this view.
  • the SHR cover disk is therefore an optional component in the sense of the invention.
  • the first blades BL1 extend with a blade profile of thickness BT1 from a first leading edge LE1 in the area of a first flow opening IN1 to a radial flow opening EX1.
  • first leading edge LE1 in the manner of designing the first blades BL1 as a splinter blade SP1 is indicated by means of a dashed line Splinter blade leading edge LES.
  • second leading edge LE2 it would be preferable for every second leading edge LE1 for the first blades BL1 and / or for the second blades BL2 (reference symbol: second leading edge LE2) to be designed as a splitter blade leading edge LES, that is to say in the form of first splitter blades SP1 and / or second splitter blades SP2 are.
  • the impeller IMP is flowed against by a process fluid PFL at a flow angle ⁇ 1 and at a speed w1.
  • the process fluid PFL is divided into two flow directions FD1, FD2, a first flow direction FD1 in the first blade channel CN1 and a second flow direction FD2 in the second blade channel CN2.
  • the proportionality of this division is also dependent on the ratio between a first radial height B11 defined by the radial blade height of the first blades BL1 in the area of the first radial flow opening IN1 to the second radial height B12 defined by the radial blade height of the second blades BL2 in the area of second axial flow opening IN2.
  • the acceleration of the process fluid PFL in the two separate blade channels CN1, CN2 is dependent on the ratio of the axial blade heights in the region of the second radial flow openings EX1, EX2.
  • the first radial flow opening EX1 is an outlet width B21 defined by means of the axial blade height of the first blades BL1
  • the second radial flow opening EX2 is a second axial outlet width defined by means of the axial blades BL2, where: 0.3 ⁇ B22 / B21 ⁇ 0.55 .
  • the invention particularly advantageously provides that a first number S1 of first blades BL1 differs from a second number S2 of second blades BL2, where: 0.5 ⁇ S2 / S1 ⁇ 2.0.
  • the first blade thickness BT1 of the first blades BL1, averaged over the blade height and profile extension, is configured differently than a second blade thickness BT2, averaged over the blade height and profile extension, of the second blades.
  • the process fluid PFL leaves the area of the radial outlet openings EX1, EX2 of the two blade channels CN1, CN2 with different deflections or with different outflow angles ⁇ 21, ⁇ 22 and different speeds w21, w22. This circumstance is due to differently shaped deflection metal angles, namely a first deflection metal angle ⁇ 1 of the first blades BL1 and a second deflection metal angle ⁇ 2 of the second blades BL2.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19154646.4A 2019-01-31 2019-01-31 Roue à aubes d'une turbomachine radiale, turbomachine radiale Withdrawn EP3690254A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19154646.4A EP3690254A1 (fr) 2019-01-31 2019-01-31 Roue à aubes d'une turbomachine radiale, turbomachine radiale

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19154646.4A EP3690254A1 (fr) 2019-01-31 2019-01-31 Roue à aubes d'une turbomachine radiale, turbomachine radiale

Publications (1)

Publication Number Publication Date
EP3690254A1 true EP3690254A1 (fr) 2020-08-05

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EP19154646.4A Withdrawn EP3690254A1 (fr) 2019-01-31 2019-01-31 Roue à aubes d'une turbomachine radiale, turbomachine radiale

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022121214A1 (de) 2022-08-23 2024-02-29 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr Verdichterlaufrad mit Verbindungen der Schaufeln untereinander für einen Radialverdichter

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5105616A (en) * 1989-12-07 1992-04-21 Sundstrand Corporation Gas turbine with split flow radial compressor
EP2025880A2 (fr) * 2007-08-16 2009-02-18 Jegel, Franz Peter, Ing. Turbocompresseur pour moteur à combustion interne
GB2485835A (en) * 2010-11-29 2012-05-30 Corac Group Plc Axially overlapping compressor impeller stages
JP2014118925A (ja) * 2012-12-19 2014-06-30 Ihi Corp 遠心圧縮機，インペラ，及びインペラの製造方法
EP3361101A1 (fr) 2017-02-10 2018-08-15 Siemens Aktiengesellschaft Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées
EP3364039A1 (fr) 2017-02-21 2018-08-22 Siemens Aktiengesellschaft Étage de retour

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5105616A (en) * 1989-12-07 1992-04-21 Sundstrand Corporation Gas turbine with split flow radial compressor
EP2025880A2 (fr) * 2007-08-16 2009-02-18 Jegel, Franz Peter, Ing. Turbocompresseur pour moteur à combustion interne
GB2485835A (en) * 2010-11-29 2012-05-30 Corac Group Plc Axially overlapping compressor impeller stages
JP2014118925A (ja) * 2012-12-19 2014-06-30 Ihi Corp 遠心圧縮機，インペラ，及びインペラの製造方法
EP3361101A1 (fr) 2017-02-10 2018-08-15 Siemens Aktiengesellschaft Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées
EP3364039A1 (fr) 2017-02-21 2018-08-22 Siemens Aktiengesellschaft Étage de retour

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022121214A1 (de) 2022-08-23 2024-02-29 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr Verdichterlaufrad mit Verbindungen der Schaufeln untereinander für einen Radialverdichter

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