EP4036378A1 - Turbomachine, en particulier expandeur radial - Google Patents

Turbomachine, en particulier expandeur radial Download PDF

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Publication number
EP4036378A1
EP4036378A1 EP21153967.1A EP21153967A EP4036378A1 EP 4036378 A1 EP4036378 A1 EP 4036378A1 EP 21153967 A EP21153967 A EP 21153967A EP 4036378 A1 EP4036378 A1 EP 4036378A1
Authority
EP
European Patent Office
Prior art keywords
flow
rotor
axis
stator
designed
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Withdrawn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
EP21153967.1A
Other languages
German (de)
English (en)
Inventor
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 EP21153967.1A priority Critical patent/EP4036378A1/fr
Publication of EP4036378A1 publication Critical patent/EP4036378A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • 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
    • 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
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical

Definitions

  • the invention relates to a turbomachine comprising a rotor mounted rotatably about an axis of rotation, the rotor comprising rotor blades, and a stator arranged around the rotor, with an inflow area for inflow of a flow medium being formed in the stator, the inflow area being formed in such a way that a flow inlet channel is formed, wherein the flow inlet channel is designed in such a way that a flow of the flow fluid runs essentially parallel to the axis of rotation, wherein the stator also has a deflection area in which the flow medium can be deflected from an axial direction into a radial direction towards the axis of rotation, wherein between the Rotor and the stator, a flow area is formed, wherein in the flow area, the energy of the flow medium can be converted into rotational energy of the rotor, with a diffuser area connected after the flow area, which is designed such that the Strömu flow medium essentially axially.
  • Flow machines for example geared machines, in particular hot gas expanders of the type mentioned at the beginning are characterized by a multi-shaft arrangement with different rotational speeds around a central drive wheel. This provides a compact unit for multi-stage compression/expansion for a large number of media, preferably gaseous media.
  • Such gear machines expand the medium, which can have an inlet temperature of up to 300°C or, in a preferred embodiment, an inlet temperature of over 300°C.
  • an inlet temperature of up to 300°C or, in a preferred embodiment, an inlet temperature of over 300°C.
  • hot gas expanders With a media inlet temperature of more than 300°C, one also speaks of so-called hot gas expanders.
  • These hot gas expanders have at least one inlet housing in which the spiral insert is arranged.
  • the spiral insert carries an adjustable inlet nozzle, the one Adjusting ring, guide vanes and bolts, the bolts serving as an axis of rotation for adjusting the guide vanes.
  • a turbomachine comprising a rotor mounted rotatably about an axis of rotation, the rotor comprising moving blades, and a stator arranged around the rotor, with an inflow region for inflow of a flow medium being formed in the stator, wherein the inflow area is designed in such a way that a flow inlet channel is formed, the flow inlet channel being designed in such a way that a flow of the flow fluid runs essentially parallel to the axis of rotation, the stator also having a deflection area in which the flow medium flows from an axial direction into a radial direction can be deflected towards the axis of rotation, with a flow area being formed between the rotor and the stator, with the energy of the flow medium being convertible into rotational energy of the rotor in the flow area, with a diffuser area adjoining the flow area, which is formed in such a way that the flow medium flows essentially axially, nozzle grid guide vanes being arranged in the flow in
  • the pivot axis can also be referred to as the axis of rotation.
  • the impeller can also be designed like a classic impeller, the impeller then being designed in such a way that the deflection takes place from the radial to the axial direction.
  • nozzle cascade guide vanes with axial inflow and outflow upstream of the impeller.
  • An essential feature of the invention is the adjustability of the nozzle grid vanes.
  • the adjustable nozzle cascade guide vanes enable control of both at a constant speed of the turbine stage the throughput as well as the pressure relief with the highest possible turbine efficiency.
  • the radial gaps above and below the axial nozzle cascade guide vanes required for adjustment should be as small as possible and only as large as necessary, since the gap flows that occur cause pressure losses and thus a reduction in turbine efficiency.
  • the concept of the axial inflow and outflow of the adjustable nozzle cascade guide vanes, on which the invention is based, enables an ultra-compact design of the radial turbine stage.
  • the special spherical contour description above and below the axial guide vanes (casing and vanes) creates minimal radial gaps in the entire adjustment range and thus minimal gaps and efficiency losses.
  • This axis is at a Radial turbomachine or, in the case of a compressor, 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 flow machine or that essentially serves as a drive or output for the operation of the flow machine.
  • 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 operation” to mean the state of operation of the corresponding machine or turbomachine, during which, for example, the rotor of the turbomachine rotates and technical work is transferred to 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 figure 1 1 shows a section of a turbomachine 1 according to the invention.
  • the turbomachine 1 comprises a rotor 2 which is mounted so as to be rotatable about an axis of rotation 4.
  • a stator 3 is arranged around the rotor 2.
  • a flow channel 5 is formed between the stator 3 and the rotor 2 .
  • the turbomachine 1 comprises an inflow area 6 which is arranged in the stator 3 and is designed for the inflow of a flow medium during operation.
  • a flow medium flows into the inflow area 6 .
  • the flow medium flows through a flow inlet channel 7.
  • the flow of the flow medium takes place here essentially parallel to the axis of rotation 4, i.e. the flow takes place essentially axially.
  • Nozzle cascade guide vanes 8 are arranged in the flow inlet channel 7 .
  • the nozzle cascade guide vanes 8 are formed about a pivot axis 9 , the pivot axis 9 running essentially parallel to a radial axis 10 related to the axis of rotation 4 .
  • the flow medium After flowing through the nozzle cascade guide vanes 8, the flow medium flows into a deflection area 11, in which the direction of flow of the flow medium is deflected from axial to radial.
  • the flow medium flows along moving blades 12 arranged on the rotor 2.
  • the moving blades 12 are arranged on the rotor surface of the rotor 2.
  • the rotor blades 12 are shaped in such a way that they essentially follow the geometry of the deflection area 11 . From about the radial flow, the flow medium is again deflected by the rotor 2 with the rotor blades 12 in the axial direction (parallel to the axis of rotation). The energy of the flow medium is converted into rotational energy of the rotor 2 in the entire blading 12 . As a result, the rotor 2 rotates.
  • the area of the rotor 2 with the moving blades 12 is also referred to as the impeller.
  • the impeller In figure 1 an open impeller is shown.
  • impeller a plurality of moving blades 12 distributed over the circumference of the rotor 2 form an impeller. Another name for the impeller is impeller.
  • the figure 1 shows two variants of an impeller.
  • a first variant of the impeller and the impeller blade 12 implemented there can be seen.
  • the moving blade 12 follows the deflection area 11.
  • the moving blades 12 are designed in such a way that a classic radial impeller is created. This means that the moving blade 12 is only formed up to the deflection area 13 and thus has a shorter radius 19 .
  • the flow medium is deflected from the axial direction into the opposite axial direction.
  • the radial installation space of the turbomachine can be significantly reduced as a result.
  • the flow medium flows through a diffuser 13 and from there out of the turbomachine in a manner not shown in detail.
  • the inlet housing Upstream of the inflow area 6, the inlet housing is designed in a spiral shape, so that the flow medium flows evenly into the inflow area 6 in the circumferential direction.
  • the flow medium is finally guided in the inflow area 6 in the axial direction in the direction of the nozzle cascade guide vanes 8 .
  • the nozzle grid guide vanes 8 are pivotable or rotatable about a pivot axis 9, so that the adjustable Nozzle cascade guide vanes 8 make it possible to regulate both the throughput and the pressure relief at a constant speed of the turbine stage with the highest possible turbine efficiency.
  • the pivot axis 9 can also be referred to as the axis of rotation. In order to ensure the most efficient adjustment possible, the necessary gaps between blade 8 and stator 3 should be as small as possible and kept constant in the adjustment range.
  • the figure 2 shows an enlarged detail of a nozzle cascade guide vane 8 from FIG figure 1 .
  • the nozzle cascade vane 8 is provided on the top and bottom with a surface which is spherical in shape, which can be described with a radius 15 (identical to radius 17) and another radius 16 (identical to 18).
  • the inner surface of the stator 3 is also spherical in the area of the blade and can be described with the radius 15 and the radius 16 .
  • the figure 3 shows a view (opposite to the direction of flow) of the flow channel 5 in the area of the flow inlet channel 7.
  • the flow channel 5 is also designed with a radius 17, the radius 17 representing an inner radius 17.
  • the outer contour of the flow channel is implemented by an outer radius 18 . (The following applies: One edge of blade 12 corresponds to radius 17 + ⁇ r 20 and the opposite edge corresponds to radius 18 - ⁇ r 20).
  • Radius 17 is identical to radius 15. Radius 18 is identical to radius 16.
  • the rotor 2 rotates with a frequency ⁇ around the rotating object 4.
  • the turbomachine 1 can be designed as a radial turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP21153967.1A 2021-01-28 2021-01-28 Turbomachine, en particulier expandeur radial Withdrawn EP4036378A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP21153967.1A EP4036378A1 (fr) 2021-01-28 2021-01-28 Turbomachine, en particulier expandeur radial

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP21153967.1A EP4036378A1 (fr) 2021-01-28 2021-01-28 Turbomachine, en particulier expandeur radial

Publications (1)

Publication Number Publication Date
EP4036378A1 true EP4036378A1 (fr) 2022-08-03

Family

ID=74346938

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21153967.1A Withdrawn EP4036378A1 (fr) 2021-01-28 2021-01-28 Turbomachine, en particulier expandeur radial

Country Status (1)

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EP (1) EP4036378A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB743782A (en) * 1952-11-07 1956-01-25 Power Jets Res & Dev Ltd Nozzle assemblies for bladed fluid flow machines such as turbines and compressors
US3365892A (en) * 1965-08-10 1968-01-30 Derderian George Turbomachine
US4821506A (en) * 1987-10-08 1989-04-18 Sundstrand Corporation Radial turbine with variable axial nozzle
DE102011119879A1 (de) * 2011-12-01 2013-06-06 Ihi Charging Systems International Gmbh Fluidenergiemaschine, insbesondere für einen Abgasturbolader eines Kraftwagens
DE102013021558A1 (de) * 2013-12-18 2014-07-24 Daimler Ag Turbine für einen Abgasturbolader einer Verbrennungskraftmaschine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB743782A (en) * 1952-11-07 1956-01-25 Power Jets Res & Dev Ltd Nozzle assemblies for bladed fluid flow machines such as turbines and compressors
US3365892A (en) * 1965-08-10 1968-01-30 Derderian George Turbomachine
US4821506A (en) * 1987-10-08 1989-04-18 Sundstrand Corporation Radial turbine with variable axial nozzle
DE102011119879A1 (de) * 2011-12-01 2013-06-06 Ihi Charging Systems International Gmbh Fluidenergiemaschine, insbesondere für einen Abgasturbolader eines Kraftwagens
DE102013021558A1 (de) * 2013-12-18 2014-07-24 Daimler Ag Turbine für einen Abgasturbolader einer Verbrennungskraftmaschine

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