EP4170182A1 - Aube de rotor pour un turbocompresseur radial - Google Patents

Aube de rotor pour un turbocompresseur radial Download PDF

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Publication number
EP4170182A1
EP4170182A1 EP21204241.0A EP21204241A EP4170182A1 EP 4170182 A1 EP4170182 A1 EP 4170182A1 EP 21204241 A EP21204241 A EP 21204241A EP 4170182 A1 EP4170182 A1 EP 4170182A1
Authority
EP
European Patent Office
Prior art keywords
impeller blade
impeller
blade tip
side wall
suction side
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Withdrawn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
EP21204241.0A
Other languages
German (de)
English (en)
Inventor
Steffen JAHRMARCHT
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 EP21204241.0A priority Critical patent/EP4170182A1/fr
Publication of EP4170182A1 publication Critical patent/EP4170182A1/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Withdrawn legal-status Critical Current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
    • 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
    • F04D29/30—Vanes
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered

Definitions

  • the invention relates to an impeller blade for an impeller of a radial turbocompressor, the impeller blade having an impeller blade tip which is opposite an inner wall of the housing during operation.
  • the invention also relates to a method for producing an impeller blade for an impeller of a radial turbocompressor, the impeller blade having an impeller blade tip which is opposite an inner wall of the housing during operation.
  • Flow machines such as turbo compressors, in particular centrifugal compressors, include, among other things, a part that can rotate about an axis of rotation and a static part that is arranged around the rotatable part.
  • a flow fluid flows into the turbomachine and is deflected there by so-called impellers. The pressure and the temperature of the flow fluid are thereby increased.
  • the impellers typically include impeller blades.
  • the impellers are the core components of a turbo compressor. Depending on the application of the compressor, different types of impellers are selected according to the requirements to be met.
  • Semi-open impellers are typically selected for applications that result in high peripheral speeds at the impeller OD. These are often applications in the area of geared compressors, but also in the area of single-shaft centrifugal compressors. Semi-open centrifugal impellers are operated with a small gap to the static part, which has a direct impact on the efficiency of the compressor.
  • the gap between the rotatable part and the static part has a major impact on the efficiency.
  • the gap between the impeller and a contour ring which is part of the static part and can also be called the stator, must be as small as possible in order to achieve the best possible efficiency.
  • an adequate gap must ensure safe operation and minimize the risk of rubbing.
  • the general conditions of the machine such as centrifugal force expansion, thermal expansion, vibrations, etc. must be taken into account when designing the gap.
  • the object of the invention is to specify an impeller blade for a centrifugal compressor which exhibits improved flow guidance during operation.
  • an impeller blade for an impeller of a radial turbocompressor having an impeller blade tip which, during operation, is opposite an inner wall of the housing, the impeller blade tip being tapered.
  • a further object of the invention is to specify a method for producing an impeller blade which exhibits improved flow guidance during operation.
  • the object directed towards the method is achieved by a method for producing an impeller blade for an impeller of a radial turbocompressor, the impeller blade having an impeller blade tip, which opposes an inner wall of the housing during operation, with the impeller blade tip being designed to be tapered.
  • the invention thus follows the path of applying an additional contour, namely a taper, adapted to the thermodynamic conditions, to the impeller blade tip of the impeller blade.
  • the impeller blade has a leading edge and a trailing edge, with the impeller blade tip being continuously tapered from the leading edge to the trailing edge.
  • the impeller blade is used on an impeller, which in turn is used in a turbo compressor, with a flow fluid flowing through the turbo compressor.
  • the flow fluid first hits the leading edge of the impeller blade and is deflected from there as a result of the profiling of the impeller blade in such a way that the flow fluid leaves the area of the impeller at the trailing edge.
  • the tapered impeller blade tip is now formed along the entire length of the impeller blade, from the leading edge to the trailing edge.
  • the impeller blade has a suction side with a suction side wall and a pressure side with a pressure side wall, the impeller blade tip having the taper both on the pressure side wall and on the suction side wall.
  • the impeller blade has a suction side with a suction side wall and a pressure side with a pressure side wall, the impeller blade tip being tapered only at the pressure sidewall.
  • the narrowing is not implemented on both sides, namely both on the suction side and on the pressure side, but only on the pressure side wall.
  • the kink which leads to a narrowing of the impeller blade tip, is therefore only formed on the pressure side.
  • the opposite suction side does not show any kink in the area of the impeller blade tip. Viewed in cross section, the suction side would accordingly be straight.
  • the impeller blade has a suction side with a suction side wall and a pressure side with a pressure side wall. wherein the impeller blade tip is tapered only on the suction sidewall.
  • the taper is not performed on both sides, namely both the suction side as well as on the pressure side, but only on the suction side wall.
  • the kink that leads to a narrowing of the impeller blade tip is therefore only formed on the suction side.
  • the opposite pressure side does not show any kink in the area of the impeller blade tip. Viewed in cross section, the pressure side would accordingly be straight.
  • the impeller blade has a central region between the leading edge and the trailing edge, with the impeller blade tip being tapered in the region of the leading edge only on the suction side wall, with the impeller blade tip having the taper in the central region both on the pressure side wall and on the suction side wall , whereby in the area of the trailing edge the impeller blade tip is tapered only on the pressure side wall.
  • the taper along the impeller blade tip from the leading edge to the trailing edge in such a way that the taper changes from the leading edge to the trailing edge, with the taper occurring on both sides in the middle.
  • the taper changes sides, first from the suction side wall to the other side, up to the pressure side wall.
  • the visible kink that leads to the taper can therefore only be seen on the suction side at the leading edge, whereas the kink at the trailing edge can only be seen on the pressure side.
  • the kink can be seen on both sides, both on the pressure side and on the suction side.
  • the impeller blade has a central region between the leading edge and the trailing edge, with the impeller blade tip being tapered only on the pressure side wall in the region of the leading edge, with in the middle area the impeller blade tip has the taper both on the pressure side wall and on the suction side wall, wherein in the area of the trailing edge the impeller blade tip is tapered only on the suction side wall.
  • the figure 1 shows a known radial flow machine in a (simplified) sectional view.
  • the turbomachine shown is a compressor, in particular a centrifugal compressor 1.
  • the turbomachine includes, among other things, a radial impeller 2 which is mounted such that it can rotate about an axis of rotation 3 .
  • the impeller 2 has an axial inflow 4 and a radial outflow 5 .
  • the impeller 2 comprises a hub 6 and impeller blades 7 protruding radially from the hub 6. Flow channels through which a flow fluid can flow are formed between the impeller blades 7. Furthermore, the hub 6 is connected to a shaft of the centrifugal compressor 1 that is not shown in the figure.
  • the impeller 2 has a wheel disc 8 which is formed in one piece with the hub 6 and connects the impeller blades 7 to one another.
  • the impeller 2 is what is known as a semi-open impeller, ie an impeller without a cover disk.
  • Alternative embodiments are also known in which the impeller 2 is a so-called closed impeller, ie an impeller with a cover disk.
  • the centrifugal compressor 1 includes a housing 9 in which the impeller 2 is placed.
  • a part of the housing 9 is designed as a spiral housing. That is, the housing 9 has a spiral housing part 10 with a spiral cavity 11 .
  • the compressor has an annular diffuser 12 which is axially symmetrical with respect to the axis of rotation 3 is designed as a hollow chamber or as a channel in the housing 9 .
  • the diffuser 12 is arranged around a circumference of the impeller 2 and is designed as a radial diffuser.
  • the diffuser 12 opens into the spiral housing part 10 or into its cavity 11.
  • an outlet diameter 13 of the impeller 2 is indicated in the form of a double arrow.
  • the diffuser 12 has a plurality of diffuser vanes 14 . That is, diffuser 12 is a vaned diffuser. In the present exemplary embodiment, the diffuser 12 has six diffuser vanes 14, of which figure 1 only two are visible. In principle, however, the diffuser 12 could also have a different number of diffuser vanes 14 .
  • the compressor 1 is used for compressing a flowing fluid such as air.
  • a flowing fluid such as air.
  • the flow fluid flows axially through the axial inflow 4 into the impeller 2 or into the flow channels formed by the impeller blades 7 .
  • the flow fluid is set in rotation by the impeller 2 and leaves the impeller 2 radially outwards through the radial outflow 5.
  • the diffuser 12 converts part of the kinetic energy of the fluid into potential energy in the form of pressure and guides the fluid into the cavity 11 of the spiral housing part 10.
  • the impeller blade 7 has an impeller blade tip 15 which is opposite an inner wall 16 of the housing. There is a gap between the impeller blade tip 15 and the inner wall 16 of the housing, which gap should be as small as possible when the centrifugal compressor 1 is in operation.
  • the flow fluid flows in the axial inflow 4 against the impeller 2 and in particular the impeller blades 7 and meets there on leading edges 17 of the impeller blades, with the flow fluid flowing along the impeller blade 7 and leaving the impeller 2 at a trailing edge 18 of the impeller blade 7 and from there into the diffuser 12 flows.
  • the figure 2 shows the impeller 2 with the individual impeller blades 7. For reasons of clarity, only two impeller blades 7 have been provided with a reference number. The impeller blades 7 are identical to each other.
  • Each impeller blade 7 has a leading edge 17 and a trailing edge 18 .
  • the leading edge 17 and the trailing edge 18 are only provided with a reference number for one impeller blade.
  • the impeller 2 rotates in the perspective view of FIG figure 2 in clockwise direction.
  • the impeller blade 7 has a suction side 19 with a suction side wall 20 and a pressure side 21 with a pressure side wall 22 .
  • suction side 19 and the suction side wall 20 as well as the pressure side 21 and the pressure side wall 22 are provided with a reference number on one impeller blade 7 .
  • the flow medium flows along the suction side wall 20 and the pressure side wall 22.
  • Each impeller blade 7 has in the figure 2 an impeller blade tip 15 which faces the casing inner wall 16 .
  • the impeller blade tip 15 is only provided with a reference number on one impeller blade 7 .
  • the figure 3 shows a section of an impeller blade 7 in a perspective view. In this case, the viewing direction is directed towards the leading edge 17 .
  • the impeller blade tip 15 is tapered. How the narrowing should ideally be designed depends on the flow conditions occurring during operation. The design of the impeller blade tip 15 depends on the result of a flow simulation, which can look different for different flow conditions.
  • the impeller blade 7 has a suction side 19 with a suction side wall 20 and a pressure side 21 with a pressure side wall 22, the impeller blade tip 15 being tapered only on the suction side wall 20 and therefore showing a taper 23.
  • the impeller blade tip 15 on the pressure sidewall 22 is formed in a straight line.
  • a squealing edge 24 is formed in a viewing direction from above onto the impeller blade tip 15 , which is opposite the inner wall 16 of the housing. The transition between the squealer 24 and the pressure sidewall 22 is substantially perpendicular.
  • the suction side wall 20 is designed essentially obliquely towards the squealer edge 24, which can be done by removing material.
  • the figure 4 shows a perspective view of the impeller blade tip 15 in a central region 35 along along the impeller blade tip 15 between the leading edge 17 and the trailing edge 18 .
  • the central region 35 is only provided with a reference number on one impeller blade 7 .
  • the figure 4 shows a section through the central area 35.
  • the figure 5 again shows the geometric conditions at the trailing edge 18.
  • the impeller blade tip 15 is designed in such a way that the impeller blade tip 15 is tapered only on the pressure side wall 22 and shows the tapering 23 there.
  • the figure 6 shows an example of the situation at the leading edge 17 in a sectional view.
  • the squealing edge 24 forms an upper end of the impeller blade tip 15 and is arranged opposite the inner wall 16 of the housing, forming a gap 26 .
  • the squealer 24 and the inner wall 16 of the housing are essentially parallel to one another at this point.
  • the impeller blade 7 has a thickness 26 and a height 27 .
  • the upper area 28 of the impeller blade 7 is referred to as the impeller blade tip 15 .
  • the taper 23 is characterized by a kink 29 which results in the thickness 26 of the impeller blade 7 becoming smaller towards the squealing edge 24 .
  • a width of the scraping edge 30 is 20% to 50%, preferably 25% to 35% of the thickness 26.
  • the upper area 28 is 1% to 10%, preferably 1 to 5%, particularly preferably 1 to 3% of the height 27 of the impeller blade 7.
  • the taper 23 is described by an inflection point 31 which, viewed mathematically, represents a change in gradient at this point.
  • the inflection point 31 can thus be referred to as a transition point at which the taper 23 changes from a convex surface to a concave surface.
  • the length of the turning point 34 is essentially 45% to 55% of the upper area 28.
  • the taper 23 is arranged on the suction side 19 in this exemplary embodiment.
  • the pressure side 21 has no taper 23 .
  • the taper 23 is arranged on the pressure side 21, with the suction side 19 having no taper here.
  • the figure 7 shows the situation in the central region 35.
  • the taper 23 is here arranged both on the pressure side 21 and on the suction side 19.
  • the blade tip 15 of the impeller is formed symmetrically to the center of the thickness 26 .
  • the geometric conditions for the pressure side 21 are essentially the same. The same conditions apply to the geometric ratio as in the case of the impeller blade tip 15 according to FIG figure 6 .
  • the figure 8 shows the situation at the trailing edge 18.
  • the impeller blade tip 15 is according to figure 6 and the impeller blade tip 15 according to figure 8 essentially the same as each other.
  • the impeller blade tip 15 of figure 6 is a mirror image of the blade tip 15 according to FIG figure 8 educated.
  • FIGS 9 to 11 show a schematic plan view of the impeller blade tip 15 seen from above. Due to the better representation, the impeller blade 7 is shown in a straight line.
  • the taper 23 is arranged on the inlet edge 17 on the suction side 19, with the taper 23 being arranged on the outlet edge 18 on the pressure side 21.
  • the taper 23 changes along the impeller blade tip 15 from the suction side 19 to the pressure side 21, with the taper 23 being formed on both sides in the middle region 35, both on the pressure side 21 and on the suction side 19.
  • the narrowing 23 is arranged on the leading edge 17 on the pressure side 21 , the narrowing 23 being arranged on the trailing edge 18 on the suction side 19 .
  • the taper 23 changes along the impeller blade tip 15 from the pressure side 21 to the suction side 19, with the taper 23 being formed on both sides in the middle region 35, both on the pressure side 21 and on the suction side 19.
  • the figure 10 shows an alternative embodiment in which the taper 23 is formed exclusively on the suction side 19 from the leading edge 17 to the trailing edge 18 .
  • the figure 11 shows an alternative embodiment in which the taper 23 is formed exclusively on the pressure side 21 from the leading edge 17 to the trailing edge 18.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP21204241.0A 2021-10-22 2021-10-22 Aube de rotor pour un turbocompresseur radial Withdrawn EP4170182A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP21204241.0A EP4170182A1 (fr) 2021-10-22 2021-10-22 Aube de rotor pour un turbocompresseur radial

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP21204241.0A EP4170182A1 (fr) 2021-10-22 2021-10-22 Aube de rotor pour un turbocompresseur radial

Publications (1)

Publication Number Publication Date
EP4170182A1 true EP4170182A1 (fr) 2023-04-26

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP21204241.0A Withdrawn EP4170182A1 (fr) 2021-10-22 2021-10-22 Aube de rotor pour un turbocompresseur radial

Country Status (1)

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EP (1) EP4170182A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050260074A1 (en) * 2004-03-23 2005-11-24 Mitsubishi Heavy Industries, Ltd Centrifugal compressor and manufacturing method for impeller
US20150086395A1 (en) * 2012-04-23 2015-03-26 Borgwarner Inc. Turbocharger blade with contour edge relief and turbocharger incorporating the same
US20180291920A1 (en) * 2015-05-15 2018-10-11 Nuovo Pignone Tecnologie Srl Centrifugal compressor impeller and compressor comprising said impeller
EP3421724A1 (fr) * 2017-06-26 2019-01-02 Siemens Aktiengesellschaft Surface portante de compresseur
EP3477059A1 (fr) * 2017-10-26 2019-05-01 Siemens Aktiengesellschaft Surface portante de compresseur

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050260074A1 (en) * 2004-03-23 2005-11-24 Mitsubishi Heavy Industries, Ltd Centrifugal compressor and manufacturing method for impeller
US20150086395A1 (en) * 2012-04-23 2015-03-26 Borgwarner Inc. Turbocharger blade with contour edge relief and turbocharger incorporating the same
US20180291920A1 (en) * 2015-05-15 2018-10-11 Nuovo Pignone Tecnologie Srl Centrifugal compressor impeller and compressor comprising said impeller
EP3421724A1 (fr) * 2017-06-26 2019-01-02 Siemens Aktiengesellschaft Surface portante de compresseur
EP3477059A1 (fr) * 2017-10-26 2019-05-01 Siemens Aktiengesellschaft Surface portante de compresseur

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