EP3408503B1 - Turbomachine avec diffuseur à aubes - Google Patents

Turbomachine avec diffuseur à aubes Download PDF

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Publication number
EP3408503B1
EP3408503B1 EP16828750.6A EP16828750A EP3408503B1 EP 3408503 B1 EP3408503 B1 EP 3408503B1 EP 16828750 A EP16828750 A EP 16828750A EP 3408503 B1 EP3408503 B1 EP 3408503B1
Authority
EP
European Patent Office
Prior art keywords
diffuser
impeller
distance
blades
rotation
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.)
Active
Application number
EP16828750.6A
Other languages
German (de)
English (en)
Other versions
EP3408503A1 (fr
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 Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
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Publication of EP3408503A1 publication Critical patent/EP3408503A1/fr
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Publication of EP3408503B1 publication Critical patent/EP3408503B1/fr
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Classifications

    • 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
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape

Definitions

  • the invention relates to a turbomachine with an impeller which is rotatably mounted about an axis of rotation, and a diffuser which has a plurality of diffuser blades, a predetermined number of diffuser blades being arranged at a first distance from the axis of rotation, the same number of diffuser blades in one is arranged second distance from the axis of rotation and the diffuser blades are arranged in the circumferential direction of the diffuser blade arrangement alternately at the first distance or second distance from the axis of rotation.
  • a diffuser is a component that slows down a fluid flow and thereby increases a fluid pressure.
  • a diffuser thus converts kinetic energy of a fluid flowing through the turbomachine into potential energy in the form of pressure.
  • bladed diffusers i.e. diffusers with diffuser blades
  • non-bladed diffusers i.e. diffusers without such blades
  • a turbomachine By using a bladed diffuser, a turbomachine can usually achieve a higher degree of efficiency than a non-bladed diffuser. Furthermore, flow instabilities can be avoided or at least reduced with the aid of a bladed diffuser, in particular in the case of partial load operation of the turbo machine.
  • turbomachines that have a bladed diffuser can be more prone to impeller damage than flow machines that have an unbladed diffuser. It may therefore be necessary in a turbomachine with a bladed diffuser to check its impeller for damage more frequently and / or to replace the impeller more frequently. As a result, high costs can arise when operating a turbomachine which has a bladed diffuser.
  • a turbomachine of the type mentioned is in each case in the publications US 2013/280060 A1 , EP 2 078 866 A1 , EP 0 280 205 A2 and U.S. 5,178,516 A disclosed.
  • One object of the invention is to provide a turbomachine that can be operated inexpensively.
  • the invention is based on the consideration that the higher susceptibility to impeller damage in a turbomachine with a bladed diffuser can be traced back to an interaction between the impeller and the diffuser or to a reaction of the diffuser blades on the impeller.
  • the diffuser blades When operating a flow machine with a bladed diffuser, the diffuser blades can cause pressure fluctuations in the fluid-filled environment of the impeller, which can cause the impeller to vibrate. It can in particular The impeller is excited at a speed-harmonic excitation of the impeller by the diffuser blades, at which the impeller is excited with an excitation frequency which corresponds to the product of the rotational speed of the impeller and the number of diffuser blades or an integral multiple of this product.
  • the excitation frequency (or one of these excitation frequencies) can in particular be of the order of magnitude of a natural frequency of the impeller.
  • a match of the excitation frequency (or one of the excitation frequencies) with a natural frequency of the impeller can lead to a resonance, in particular if an oscillation form of such a diffuser-related excitation corresponds to a natural form of the impeller.
  • resonance high vibration amplitudes of the impeller can occur, which under certain circumstances lead to a fatigue failure of the impeller.
  • the excitation intensity can depend, among other things, on the speed of the impeller, a fluid density and / or a fluid pressure at the inlet of the turbomachine.
  • a diffuser-related excitation of the impeller can become critical, particularly in the case of a high-pressure compressor.
  • the invention is further based on the knowledge that because at least two of the diffuser blades are arranged at different distances from the axis of rotation (i.e. at different distances from the axis of rotation), a less regular interaction between the diffuser blades and the impeller can be achieved. This in turn enables the diffuser-related excitation of the impeller to be reduced. Because at least two of the diffuser blades are arranged at different distances from the axis of rotation, in particular an amplitude of the excitation can be reduced and / or the probability of an excitation frequency being matched with a natural frequency of the impeller can be reduced.
  • the said arrangement of the diffuser blades in the turbomachine can reduce the susceptibility to damage to the impeller. This in turn enables the impeller to be checked for damage less frequently and / or the impeller to be replaced less frequently. Consequently, the turbo machine can be operated inexpensively.
  • the invention makes it possible to reduce the excitation potential for impeller vibrations and thereby advantageously to obtain a high efficiency of the turbo machine.
  • the distance between its leading edge and the axis of rotation can be understood as the distance between a diffuser blade and the axis of rotation.
  • the leading edge can in turn be understood to mean that edge of the respective diffuser blade which delimits a fluid inlet of the arrangement of the diffuser blades (diffuser blade arrangement).
  • the leading edge is expediently that edge of the respective diffuser blade which is closest to the impeller.
  • the axis of rotation can be a geometric (imaginary) axis.
  • the axis of rotation expediently coincides with the longitudinal direction of a shaft to which the impeller is connected.
  • the diffuser blades are preferably arranged in a ring.
  • the diffuser blades can be arranged in such a way that they form a ring.
  • the diffuser is arranged downstream of the impeller. That is, when the turbo machine is in operation, a volume element of a fluid flowing through the turbo machine expediently flows first through the impeller and then through the diffuser. It is also advantageous if the diffuser is arranged around a circumference of the impeller.
  • the diffuser can be formed, among other things, by non-rotating annular walls which preferably adjoin an outlet of the impeller radially.
  • the diffuser is expediently spaced from the impeller by a gap.
  • the diffuser blades can be shaped as desired.
  • the diffuser blades can be flat or curved.
  • the diffuser blades can be profiled. That is, the diffuser blades can have a predetermined profile.
  • the diffuser blades can optionally be adjusted with regard to their orientation.
  • the impeller is preferably a radial impeller.
  • the impeller can therefore be set up to guide the fluid in the turbomachine radially, in particular radially outwards.
  • the impeller is advantageously equipped with radial impeller blades.
  • the diffuser is a radial diffuser. That is to say, the diffuser can be set up to guide the fluid in the turbomachine radially, in particular radially outward.
  • the turbomachine can be a semi-axial turbomachine, among other things.
  • the turbomachine is preferably a radial turbomachine.
  • turbomachine is a radial compressor.
  • one diffuser blade is arranged at the first distance from the axis of rotation, while the other diffuser blade is arranged at the second distance from the axis of rotation.
  • different distances from the axis of rotation are provided.
  • a predetermined number of diffuser blades is arranged at the first distance from the axis of rotation.
  • the same number of diffuser blades is arranged at the second distance from the axis of rotation.
  • the diffuser has an even number of diffuser blades, so that 50% of the diffuser blades are arranged at the first distance from the axis of rotation. The other 50% of the diffuser blades are arranged at the second distance from the axis of rotation.
  • n diffuser blades at a first distance from the axis of rotation and n diffuser blades at a second distance from the axis of rotation, where n is a natural number and 2 * n is the number of diffuser blades.
  • the diffuser blades are arranged alternately with regard to their distance from the axis of rotation.
  • one of the diffuser blades is arranged at the first distance from the axis of rotation.
  • the diffuser blade following this diffuser blade in the circumferential direction of the diffuser blade arrangement is arranged at a second distance from the axis of rotation.
  • the diffuser blade following the last-mentioned diffuser blade in the circumferential direction of the diffuser blade arrangement is in turn arranged at the first distance from the axis of rotation and so on.
  • the diffuser blades are arranged alternately in the circumferential direction at the first and second distance from the axis of rotation.
  • the second distance is at least 10% larger than the first distance.
  • the percentage difference between the first and the second distance can be selected, inter alia, as a function of the number of diffuser blades, the number of impeller blades and / or a nominal speed of the impeller.
  • the first distance preferably corresponds to at least 0.525 times an outlet diameter of the impeller. It can thereby be achieved that said reaction of the diffuser blades on the impeller is kept low. A smaller amount of the first distance could lead to an undesirably strong reaction of the diffuser blades on the impeller.
  • a diameter of the impeller at its outlet can be understood as the exit diameter of the impeller.
  • the second distance corresponds to at most 0.65 times the outlet diameter of the impeller. In this way, a deterioration in the efficiency of the diffuser - caused by a large amount of the second distance - can be avoided or at least reduced.
  • the diffuser blades have a blade solidity of at most 1, in particular of at most 0.7.
  • a diffuser is also referred to as a "low solidity diffuser”.
  • the ratio of the profile chord length of the respective diffuser blade can be used as the blade overlap for the circumferential pitch of the diffuser blade arrangement. With such a diffuser, a good efficiency of the turbomachine can also be achieved when the turbomachine is not operated at its design point.
  • the turbo machine can be a multi-stage turbo machine. That is to say, the turbo machine can have several impellers arranged one behind the other, which in particular can be arranged on a common shaft. Furthermore, the turbomachine can have its own diffuser for each of the impellers. Furthermore, each of the diffusers can be configured as described above.
  • FIG 1 shows a radial turbomachine 2 in a (simplified) sectional view.
  • the turbomachine 2 shown is a radial compressor.
  • the turbomachine 2 includes, inter alia, a radial impeller 4, which is mounted rotatably about an axis of rotation 6.
  • the impeller 4 has an axial impeller inlet 8 and a radial impeller outlet 10.
  • the impeller 4 comprises a hub 12 and impeller blades 14 protruding radially from the hub 12. Flow channels through which a fluid can flow are formed between the impeller blades 14. Furthermore, the hub 12 is connected to a shaft of the turbomachine 2 (not shown in the figures).
  • the impeller 4 has a wheel disk 16 which is formed in one piece with the hub 12 and connects the impeller blades 14 to one another.
  • the impeller 4 is a so-called open impeller, that is to say an impeller without a cover plate.
  • the impeller 4 could be a so-called closed impeller, that is to say an impeller with a cover disk.
  • the turbomachine 2 comprises a housing 18 in which the impeller 4 is placed.
  • Part of the housing 18 is designed as a spiral housing. That is to say, the housing 18 has a spiral housing part 20 with a spiral-shaped cavity 22.
  • the turbomachine 2 also has an annular diffuser 24 which is axially symmetrical with respect to the axis of rotation 6 and which is designed as a hollow chamber or as a channel in the housing 18.
  • the diffuser 24 is arranged around a circumference of the impeller 4 and is designed as a radial diffuser.
  • the diffuser 24 opens into the spiral housing part 20 or into its cavity 22.
  • an outlet diameter 26 of the impeller 4 is identified in the form of a double arrow.
  • the diffuser 24 has a plurality of diffuser blades 28. That is, the diffuser 24 is a bladed diffuser. In the present exemplary embodiment, the diffuser 24 has six diffuser blades 28 (cf. FIG 2 ), of which in FIG 1 only two are recognizable.
  • the diffuser 24 could also have a different number of diffuser blades 28.
  • the diffuser blades 28 are arranged alternately at a first distance (measured between an inlet edge 30 of the respective diffuser blade 28 and the axis of rotation 6) or a second distance (measured between an inlet edge 30 of the respective diffuser blade 28 and the axis of rotation 6) to the axis of rotation 6.
  • the two in FIG 1 The diffuser blades 28 shown are each arranged at a first distance 32 from the axis of rotation 6.
  • the turbo machine 2 is used to compress a fluid such as air.
  • a fluid such as air.
  • the fluid flows axially through the impeller inlet 8 into the impeller 4 or into the flow channels formed by the impeller blades 14.
  • the fluid is set in rotation by the impeller 4 and leaves the impeller 4 radially outward through the impeller outlet 10.
  • the diffuser 24 converts part of the kinetic energy of the fluid into potential energy in the form of pressure and guides the fluid into the cavity 22 of the volute casing part 20.
  • FIG. 8 shows an arrangement of the diffuser blades 28 of the turbomachine 2 from FIG FIG 1 in a front view, the representation not being true to scale.
  • the aforementioned axis of rotation 6 of the turbomachine 2 runs perpendicular to the plane of the drawing FIG 2 .
  • FIG 2 It also shows FIG 2 the wheel disk 16 of the impeller 4 from FIG 1 .
  • the diffuser vanes 28 are shown as planar vanes. In principle, the diffuser blades 28 can have any shape.
  • the diffuser blades 28 are arranged alternately with regard to their distance from the axis of rotation 6. That is to say, three of the six diffuser blades 28 are arranged at the first distance 32 from the axis of rotation 6. The remaining three diffuser blades 6, which are each arranged in the circumferential direction 36 of the diffuser blade arrangement between two of these three diffuser blades 28, are arranged at a second distance 34 from the axis of rotation 6.
  • the first-mentioned three diffuser blades 28 touch an (imaginary) circle with their respective leading edge 30, the radius of which corresponds to the first distance 32.
  • the other three diffuser blades 28, on the other hand touch an (imaginary) circle with their respective leading edge 30, the radius of which corresponds to the second distance 34.
  • the axis of rotation 6 runs through the common center point of both circles.
  • the first distance 32 corresponds to 0.565 times the outlet diameter 26 of the impeller 4, while the second distance 34 corresponds to 0.625 times the outlet diameter 26 of the impeller 4.
  • the second distance 34 is approximately 10.6% greater than the first distance 32.
  • the diffuser blades 28 lead to pressure fluctuations in the fluid-filled environment of the impeller 4, which cause the impeller 4 to vibrate.
  • the above-described arrangement of the diffuser blades 28 causes a less regular interaction between the diffuser blades 28 and the impeller 4 (compared to a diffuser whose diffuser blades are all arranged at the same distance from the axis of rotation). This in turn leads to a reduction in the diffuser-related excitation of the impeller 4 (compared to a diffuser whose diffuser blades are all arranged at the same distance from the axis of rotation). Especially an amplitude of the excitation and the probability of an excitation frequency coinciding with a natural frequency of the impeller 4 are reduced.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (6)

  1. Turbomachine (2) ayant une roue (4), qui est montée tournante autour d'un axe (6) de rotation et un diffuseur (24) qui a une pluralité d'aubes (28) de diffuseur, dans laquelle au moins l'une des aubes (28) de diffuseur est disposée à une première distance de l'axe (6) de rotation et au moins une autre des aubes (28) de diffuseur est disposée à une deuxième distance (34) de l'axe (6) de rotation, dans laquelle un nombre donné à l'avance d'aubes (28) de diffuseur est disposé à la première distance (32) de l'axe (6) de rotation, le même nombre d'aubes (28) de diffuseur est disposé à la deuxième distance (34) de l'axe (6) de rotation, et les aubes (28) de diffuseur sont disposées, dans la direction (36) périphérique de l'agencement d'aubes de diffuseur, en alternance à la première distance (32) et à la deuxième distance (34) de l'axe (6) de rotation,
    dans laquelle la deuxième distance (34) est plus grande d'au moins 10% que la première distance (32),
    caractérisée en ce que
    toutes les aubes (28) de diffuseur sont constituées pareillement.
  2. Turbomachine (2) suivant la revendication 1,
    caractérisée en ce que
    la roue (4) est une roue radiale et le diffuseur (24) est un diffuseur radial.
  3. Turbomachine (2) suivant la revendication 1 ou 2, caractérisée en ce que la turbomachine (2) est un compresseur radial.
  4. Turbomachine (2) suivant l'une des revendications précédentes, caractérisée en ce que la première distance (32) correspond au moins à 0,525 fois un diamètre (26) de sortie de la roue (4).
  5. Turbomachine (2) suivant l'une des revendications précédentes, caractérisée en ce que la deuxième distance (34) correspond au plus à 0,65 fois un diamètre (26) de la roue (4) .
  6. Turbomachine (2) suivant l'une des revendications précédentes, caractérisée en ce que les aubes (28) de diffuseur ont un chevauchement d'aubes de 1 au plus, notamment de 0,7 au plus.
EP16828750.6A 2016-01-28 2016-12-29 Turbomachine avec diffuseur à aubes Active EP3408503B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016201256.8A DE102016201256A1 (de) 2016-01-28 2016-01-28 Strömungsmaschine mit beschaufeltem Diffusor
PCT/EP2016/082817 WO2017129342A1 (fr) 2016-01-28 2016-12-29 Turbomachine à diffuseur à aubes

Publications (2)

Publication Number Publication Date
EP3408503A1 EP3408503A1 (fr) 2018-12-05
EP3408503B1 true EP3408503B1 (fr) 2021-04-07

Family

ID=57838334

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16828750.6A Active EP3408503B1 (fr) 2016-01-28 2016-12-29 Turbomachine avec diffuseur à aubes

Country Status (3)

Country Link
EP (1) EP3408503B1 (fr)
DE (1) DE102016201256A1 (fr)
WO (1) WO2017129342A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015219556A1 (de) 2015-10-08 2017-04-13 Rolls-Royce Deutschland Ltd & Co Kg Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
DE102017203230A1 (de) * 2017-02-28 2018-08-30 Siemens Aktiengesellschaft Diffusor
EP3460255A1 (fr) 2017-09-20 2019-03-27 Siemens Aktiengesellschaft Système pouvant être traversé
EP3460257A1 (fr) 2017-09-20 2019-03-27 Siemens Aktiengesellschaft Dispositif pouvant être traversé
EP3460256A1 (fr) 2017-09-20 2019-03-27 Siemens Aktiengesellschaft Dispositif pouvant être traversé
DE102018107264A1 (de) * 2018-03-27 2019-10-02 Man Energy Solutions Se Radialverdichter und Turbolader
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine

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DE3705307A1 (de) * 1987-02-19 1988-09-01 Kloeckner Humboldt Deutz Ag Radialverdichter
US5178516A (en) * 1990-10-02 1993-01-12 Hitachi, Ltd. Centrifugal compressor
JP3356510B2 (ja) * 1992-12-25 2002-12-16 株式会社荏原製作所 遠心又は斜流形ポンプの羽根付きディフューザ
DE4309479A1 (de) * 1993-03-24 1994-09-29 Wilo Gmbh Radialkreiselpumpe
EP1757814A1 (fr) * 2005-08-26 2007-02-28 ABB Turbo Systems AG Compresseur centrifuge
JP4795912B2 (ja) * 2006-10-30 2011-10-19 三菱重工業株式会社 可変ディフューザ及び圧縮機
US20130280060A1 (en) * 2012-04-23 2013-10-24 Shakeel Nasir Compressor diffuser having vanes with variable cross-sections

Non-Patent Citations (1)

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Also Published As

Publication number Publication date
EP3408503A1 (fr) 2018-12-05
DE102016201256A1 (de) 2017-08-03
WO2017129342A1 (fr) 2017-08-03

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