EP4015829A1 - Turbomachine radiale, en particulier compresseur - Google Patents

Turbomachine radiale, en particulier compresseur Download PDF

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Publication number
EP4015829A1
EP4015829A1 EP20215308.6A EP20215308A EP4015829A1 EP 4015829 A1 EP4015829 A1 EP 4015829A1 EP 20215308 A EP20215308 A EP 20215308A EP 4015829 A1 EP4015829 A1 EP 4015829A1
Authority
EP
European Patent Office
Prior art keywords
area
compressor
flow
flow fluid
compression
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Withdrawn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
EP20215308.6A
Other languages
German (de)
English (en)
Inventor
Jörg Paul HARTMANN
Werner Jonen
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 EP20215308.6A priority Critical patent/EP4015829A1/fr
Publication of EP4015829A1 publication Critical patent/EP4015829A1/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Withdrawn legal-status Critical Current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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/02—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal
    • F04D17/025—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal comprising axial flow and radial flow stages
    • 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
    • F04D17/02—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal
    • 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
    • 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
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4226—Fan casings
    • F04D29/4253—Fan casings with axial entry and discharge

Definitions

  • the invention relates to a compressor comprising a rotor mounted so as to be rotatable about an axis of rotation, a stator arranged around the rotor, with a flow channel being formed between the stator and the rotor, with a flow fluid inlet which is formed for the essentially axial flow of a flow fluid into the flow channel , further comprising a first compression area for compressing the flow fluid, the first compression area having rotor blades, wherein in the first compression area a flow deflection of the flow fluid takes place from the essentially axial direction into an essentially radial direction, the radial direction and the axial direction being one relate to the axis of rotation, further comprising a deflection area for deflecting the flow fluid flowing out of the first compression area, the deflection area having guide vanes.
  • Compressors are machines that apply mechanical work to an enclosed gas, compressors being used to compress gases. This increases the pressure and density of the gas. Another term for compressor is compressor.
  • Compressors can be designed, inter alia, as so-called geared compressors or centrifugal compressors. Further embodiments of compressors are also known. For example, axial compressors are known.
  • turbomachines are also generally known, which can also be designed as radial turbomachines.
  • Centrifugal turbomachines are known as either centrifugal turbocompressors or centrifugal turboexpanders. Unless otherwise stated, the following explanations refer to the compressor version.
  • the invention can be used for expanders or turbines in the same way as for compressors, with a radial turboexpander being opposite a radial turbo compressor essentially provides a reverse flow direction of the flow fluid.
  • the global market environment demands turbo machines with low investment costs. To reduce costs, it is particularly effective to make the machines more compact. It is particularly important to reduce the required radial or axial space. This measure is usually accompanied by a deterioration in efficiency.
  • centrifugal compressor stage The task of a centrifugal compressor stage is generally to supply energy to the flow fluid with the highest possible efficiency and to convert this into pressure.
  • stages consisting of impeller and stator components are necessary to achieve the desired increase in pressure. It is obvious that a turbomachine can be built more cheaply the fewer stages are used for the desired pressure increase. Therefore, the power density per stage should be maximized at acceptable efficiencies. This could be done, for example, by increasing the speed or peripheral speed.
  • the invention has set itself the task of improving the compactness without impairing the aerodynamics disproportionately.
  • a compressor comprising a rotor mounted rotatably about an axis of rotation, a stator arranged around the rotor, a flow channel being formed between the stator and the rotor, with a flow fluid inlet for the essentially axial flow of a flow fluid into the flow channel educated further comprising a first compression area for compressing the flow fluid, the first compression area having rotor blades, wherein in the first compression area a flow deflection of the flow fluid takes place from the essentially axial direction into an essentially radial direction, the radial direction and the axial direction being the same relate to the axis of rotation, further comprising a deflection area for deflecting the flow fluid flowing out of the first compression area, wherein the deflection area has guide vanes, further comprising a second compression area for further compressing the flow fluid flowing out of the deflection area, further comprising an outflow area, wherein the flow fluid from the second compression area flows into the outflow area.
  • this axis is also the axis of rotation of a rotor or the shaft with the impellers.
  • the flow guide deflects the process fluid in an arc, so that when referring to the deflection, the term "radial” does not refer to the central axis, but to the bend or curvature of the deflection itself.
  • a process fluid to be conducted is generally the flow fluid that is conveyed by the corresponding turbomachine or radial turbomachine or that essentially serves as a drive or output for the operation of the turbomachine.
  • the process fluid to be conducted is the medium that mainly either gives off or absorbs significant technical work.
  • the invention understands the term “in an operation” to mean the state of operation of the corresponding machine or turbomachine, during which, for example, the rotor of the machine rotates and a transmission of technical work onto the flow fluid or away from the flow fluid.
  • the invention understands a moving blade to mean rotating blading.
  • Such rotating blading can be designed as an impeller that is shrunk onto a shaft, for example.
  • the running stage it is possible for the running stage to consist of individual blades which are either attached to a shaft of a rotor or are even formed in one piece with the rotor or the shaft.
  • a guide vane means static blading.
  • Such static blading can be designed as a ring of guide vanes, which is attached, for example, to the interior of a housing.
  • the invention proposes to carry out a double compression instead of a single compression.
  • a stage concept is proposed here with which it is possible to significantly increase the energy density per stage.
  • the energy supplied can be increased overall at constant speeds.
  • a known overhanging geared compressor stage could be replaced by a combination radial and axial stage on a pinion shaft end along with a very compact volute.
  • the radial stage is designed in such a way that the radial impeller does not flow radially but axially and flows directly to the guide wheel of the first axial stage without the typical radial diffuser.
  • the axial stage is designed in such a way that the guide wheel has pure deflection blading and applies a high counter-rotation to the subsequent rotor blading.
  • the compressor can be used for gas applications with smaller molecular weights such as hydrogen gas, natural gas or the like.
  • the rotor blading can be designed on the outlet side in such a way that a certain residual swirl remains for the use of a compact spiral or a swirl-free outflow for an outlet casing results.
  • the blades can be an integral part of the rotor, which can be achieved using additive manufacturing methods.
  • stage concept which, if the Mach numbers in the flow area are very low and the mechanical load capacity limits the speed, can significantly increase the energy density per stage.
  • the guide vanes are designed in such a way that a change in a velocity component of the flow fluid takes place in the circumferential direction.
  • the second compression area has additional, second moving blades, which are arranged on the rotor.
  • the outflow area is designed in a spiral shape.
  • the flow fluid is deflected from the axial direction into a radial direction in the first compression region. After this deflection, the flow medium is again deflected from the radial to the axial direction, so that the flow medium flows out of the first compression region essentially in the axial direction.
  • the deflection area and the second compression area are arranged axially one behind the other.
  • the deflection area and the second compression area are arranged in a multi-stage single-shaft compressor.
  • the first compression area is advantageously designed in such a way that the flow fluid is deflected from an axial direction into a radial direction and flows out radially from the first compression area.
  • the blading does not deflect to a twist-free flow of 0°, but to a counter-twist that essentially corresponds to the twist of the inflow. Aerodynamically, this is possible through a thickness design of the blade, which avoids deceleration during deflection.
  • the counter-rotation present behind the deflection blading can then be used in a second row of blades located downstream, which can be part of the impeller, ie is connected to the first row of blades, in order to supply further energy to the flow fluid.
  • a skilful choice of the outflow angle in connection with the peripheral speed at the blade outlet can also generate a swirl-free inflow for the next impeller.
  • the flow fluid is deflected in the deflection area essentially by 180°.
  • the figure 1 shows a schematic longitudinal section along an x-axis in a compressor 1 according to the invention figure 1 shows only a section of the compressor 1.
  • the in figure 1 The compressor 1 shown can also be referred to as a radial turbo compressor.
  • the compressor 1 comprises a rotor 3 that is rotatably mounted about an axis of rotation 2.
  • the compressor shown can also be applied in a geared compressor at a stage position.
  • the rotor 3 has a cavity 4 .
  • Rotor blades 6 are arranged on a rotor surface 5 of the rotor 3 .
  • This Rotor blades 6 are arranged regularly in a circumferential direction 7 and form what is known as an impeller 27.
  • a stator 8 is arranged around the rotor 3 . As a result, a flow channel 9 is formed between the stator 8 and the rotor 3 . A first compression region 10 is formed between the stator 8 and the rotor 3 .
  • This compression area 10 comprises a flow fluid inlet 11 through which a process fluid or a flow fluid flows during operation.
  • This flow is represented symbolically by the arrow 12 .
  • the flow fluid flows from a substantially axial direction 13, ie substantially parallel to the axis of rotation 2 into the flow inlet 11.
  • the flow fluid undergoes a deflection from the axial direction 13 into a radial direction 20.
  • the deflection from the axial direction 13 into the radial direction 20 does not necessarily have to take place by 90°.
  • the deflection can be less than 90°. In the figure 1 deflection shown is approx. 45°.
  • the flow fluid flows through a deflection area 14 which is formed by guide vanes 15 which are arranged inside the stator 8 in the circumferential direction 7 .
  • the flow fluid is thereby deflected.
  • This compression area 16 is formed with further rotor blades 17 on the rotor surface 5.
  • the flow fluid flows into a spiral outflow area 18.
  • the flow fluid is deflected in the circumferential direction 7.
  • the flow fluid then flows out of the stator 8 (not shown).
  • a drive machine is coupled to the rotor 2 in a torque-transmitting manner.
  • the prime mover is in the figure 1 not shown. Energy is transferred to the flow fluid by the drive machine, so that the flow fluid is compressed in the first compression region 10, ie the pressure is increased. The pressure of the flow fluid is further increased in the further course in the compressor 1 through the deflection area 14 and the second compression area 16 .
  • the rotor blades 6 in the first compression area 10 and the rotor blades 17 in the second compression area 16 are designed accordingly.
  • the radial space in the figure 1 shown compressor 1 is thereby reduced.
  • the embodiment of the compressor 1 shown is designed with a radius R1, this radius R1 being the distance from the axis of rotation 2 to the rotor surface 5 after the moving blade 17.
  • the rotor 3 is designed in such a way that the radius 3 is reduced, so that the spiral-shaped outflow area 18 is arranged in the direction of the axis of rotation 2 as seen in the direction of flow.
  • a seal 21 for example a labyrinth seal 19 , is formed between the stator 8 and the rotor 3 .
  • the guide vanes 15 are designed in such a way that a speed component of the flow fluid changes in the circumferential direction 7 , with the circumferential direction 7 relating to the axis of rotation 2 .
  • FIG 12 shows two versions of an alternative embodiment of the invention.
  • the second variant is shown in dashed lines.
  • the inside figure 2 shown compressor 1 is essentially the same design as the compressor 1 from figure 1 .
  • the difference between the compressor 1 from figure 1 and compressor 1 off figure 2 lies in the design of the outflow area 18.
  • the outflow area is directed downwards (towards the rotor 2).
  • This radially inwardly formed first outflow area 22 is similar to the outflow area 18 from FIG figure 1 , except that the hollow-shaped rotor 2 is formed in such a way that the first outflow region 22 lies between the second moving blades 17 and the axis of rotation 2 .
  • the first outflow area 22 thus protrudes as far as the deflection area 14.
  • a spiral wound outwards can also be designed according to a second variant, as shown in dashed lines in FIG.
  • the figure 3 shows a radial compressor stage designed as a compressor 1 of a multi-stage radial shaft compressor according to the prior art.
  • the compressor 1 according to figure 3 comprises a rotor 3 and a stator 8.
  • a flow channel 9 is formed between the rotor 3 and the stator 8, with the flow channel 9 deflecting the flow fluid in the first compression region 10 from the axial direction 11 into the radial direction 20.
  • the flow fluid is then deflected from the radial direction 20 back into the axial direction 11 and then back into the radial direction 20 .
  • the flow fluid is thus deflected by 180°, where it then flows through guide vanes 26 and the twist is removed there by deflection.
  • the flow fluid then flows essentially in the axial direction 11 to an outflow region which is in the figure 3 is not shown in detail.
  • the figure 4 shows an alternative embodiment of a compressor 1 according to the invention and is based on the embodiment according to FIG figure 3 .
  • the inside figure 4 Compressor 1 shown comprises a rotor 3 and a stator 8 arranged around the rotor 3.
  • the difference between the compressor 1 and FIG figure 3 to the compressor 1 from the figures 1 and 2 is that in the first compression region 10 the direction of flow of the flow fluid is essentially deflected from the axial direction 13 into the radial direction 20 .
  • the impeller 27 embodied with rotor blades 6 is embodied in such a way that the flow fluid is deflected from the axial direction 13 into the radial direction 20 .
  • the deflection area 14 is designed in such a way that the flow fluid is deflected from the radial direction 20 into the axial direction 11 and then back into the radial direction 20 .
  • the flow fluid is deflected once by 180° in relation to the rotor axis.
  • the flow fluid flows into the second compression area 16, which is formed in a radial direction 20.
  • Guide vanes 15 are arranged in the deflection area 14 . These guide vanes 15 are designed in such a way that the flow fluid can be deflected in the circumferential direction.
  • the second compression region 16 is designed in such a way that the flow fluid is deflected from a radial direction 20 into a substantially axial direction 11 and the twist is removed in the process.
  • the rotor 3 is solid (without a cavity). In an alternative embodiment, the rotor 3 can be formed with a cavity 4 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP20215308.6A 2020-12-18 2020-12-18 Turbomachine radiale, en particulier compresseur Withdrawn EP4015829A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20215308.6A EP4015829A1 (fr) 2020-12-18 2020-12-18 Turbomachine radiale, en particulier compresseur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20215308.6A EP4015829A1 (fr) 2020-12-18 2020-12-18 Turbomachine radiale, en particulier compresseur

Publications (1)

Publication Number Publication Date
EP4015829A1 true EP4015829A1 (fr) 2022-06-22

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ID=73855686

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EP20215308.6A Withdrawn EP4015829A1 (fr) 2020-12-18 2020-12-18 Turbomachine radiale, en particulier compresseur

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EP (1) EP4015829A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19523661A1 (de) * 1995-06-29 1997-01-02 Mayer Helmut Turborotor
WO2013141912A2 (fr) * 2012-02-16 2013-09-26 Carrier Corporation Compresseurs hybrides et systèmes de compression
EP3540236A1 (fr) * 2018-03-16 2019-09-18 Carrier Corporation Compresseur à flux mixte de système de réfrigération
EP3633202A1 (fr) * 2018-10-03 2020-04-08 Danfoss A/S Compresseur cvca avec des étapes de compression mixte et radiale

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19523661A1 (de) * 1995-06-29 1997-01-02 Mayer Helmut Turborotor
WO2013141912A2 (fr) * 2012-02-16 2013-09-26 Carrier Corporation Compresseurs hybrides et systèmes de compression
EP3540236A1 (fr) * 2018-03-16 2019-09-18 Carrier Corporation Compresseur à flux mixte de système de réfrigération
EP3633202A1 (fr) * 2018-10-03 2020-04-08 Danfoss A/S Compresseur cvca avec des étapes de compression mixte et radiale

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