US20140126994A1 - Radial gas expander - Google Patents

Radial gas expander Download PDF

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Publication number
US20140126994A1
US20140126994A1 US14/125,990 US201214125990A US2014126994A1 US 20140126994 A1 US20140126994 A1 US 20140126994A1 US 201214125990 A US201214125990 A US 201214125990A US 2014126994 A1 US2014126994 A1 US 2014126994A1
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United States
Prior art keywords
introduction channel
gas expander
gas
casing
rotating shaft
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Abandoned
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US14/125,990
Inventor
Hiroki Ishikawa
Hideki Nagao
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Mitsubishi Heavy Industries Compressor Corp
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Mitsubishi Heavy Industries Compressor Corp
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Assigned to MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION reassignment MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ISHIKAWA, HIROKI, NAGAO, HIDEKI
Publication of US20140126994A1 publication Critical patent/US20140126994A1/en
Abandoned 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/12—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines with repeated action on same blade ring
    • F01D1/14—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines with repeated action on same blade ring traversed by the working-fluid substantially radially
    • 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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a radial gas expander (a radial flow gas expander) in which impellers are arranged on a single shaft in multiple stages.
  • the gas expander is used to suction and expand high pressure gas discharged from a plant, convert pressure energy of the gas into speed energy (mechanical energy), and thus, recover power and reduce the power of a driving motor or the like.
  • a gas expander which corresponds to higher pressure energy has been required.
  • a radial gas expander in which a plurality of impellers is provided in multiple stages is known.
  • a geared (speed-increasing gear) radial gas expander is known, which is configured of a driving gear, a speed-increasing gear configured of a pinion gear engaging with the driving gear, and a plurality of impellers disposed in a pinion shaft (for example, refer to Patent Document 1).
  • a radial gas expander in which the plurality of impellers are arranged between bearings on a single shaft and the impellers are built in a single casing.
  • the shaft is the single shaft in spite of including the multistage impeller. Accordingly, compared to the geared radial gas expander or the like, the number of high-pressure seals or high-pressure casing can be reduced to a minimum, and a radial gas expander having high reliability can be realized even in a higher pressure condition (for example, refer to Patent Document 2).
  • a radial gas expander 101 of the related art includes a casing 2 , a rotating shaft 3 which is rotatably provided in the casing 2 , and a plurality of impellers 4 which are fixed to the rotating shaft 3 .
  • the radial gas expander 101 includes two gas expander sections 105 a and 105 b to expand the gas in the inner portion of the gas expander.
  • the casing 2 is configured of a casing main body 6 and a diaphragm group 7 including a plurality of diaphragms which are built in the casing main body 6 and integrally connected.
  • the gas expander sections 105 a and 105 b are configured to connect a plurality of diaphragms 8 , 9 a, 9 b, 10 a, 10 b , 11 a, 11 b, 12 a, 12 b, 13 a, and 13 b, in which return bends connecting stages are formed, in an axial direction.
  • the expander section 105 a and 105 b includes gas introduction channels 120 a and 120 b communicating with suction ports 18 a and 18 b of the casing 2 and gas outflow channels 21 a and 21 b communicating with discharge ports 19 a and 19 b of the casing 2 in each section.
  • the gas introduction channels 120 a and 120 b are defined between the center diaphragm 8 which is provided in the center between two gas expander sections 105 a and 105 b and diaphragms 9 a and 9 b which are nearest to the center among the plurality of diaphragms except for the center diaphragm 8 .
  • Nozzle blades 24 which generate a gas flow corresponding to profiles of the impellers 4 , are provided in the upstream side of the impellers 4 on the gas introduction channel 120 .
  • the gas is introduced to the other gas expander section 105 b via gas pipes 22 and the suction port 18 b and is further expanded.
  • spacers 125 are installed in the upstream sides of the nozzle blades 24 of the gas introduction channels 120 a and 120 b.
  • Patent Document 1 Japanese Patent No. 3457828
  • Patent Document 2 Japanese Unexamined Patent Application, First Publication No. 2011-43070
  • the spacers 125 are installed in the upstream sides of the nozzle blades 24 , there is a problem that a flow of the gas flowing into the nozzle blades 24 is disturbed. As shown in FIG. 6 , when a streamline L of the introduced gas is disturbed by the spacers 125 , loss occurs when the gas flows into the nozzle blades 24 . Moreover, since the spacers are installed in the vicinity of inlets of the gas introduction channels 120 a and 120 b, reduction effects of an introduction channel width change are decreased due to differential pressure. Accordingly, a gas flow rate is changed according to the change of the channel width, a desired gas flow rate is not generated when the gas flows into the nozzle blades 24 , and loss occurs. In this way, the spacers 125 impede expansion performance of the impellers 4 , and furthermore, a decrease in the performance of the radial gas expander 101 occurs.
  • the present invention is made in consideration of the above-described circumstances, and an object thereof is to provide a radial gas expander capable of obtaining a desired performance. Moreover, an object thereof is to provide a radial gas expander capable of securing the channel widths of the gas introduction channels 120 a and 120 b and preventing walls of diaphragms configuring the casing from being deformed.
  • the present invention provides the following means.
  • a radial gas expander includes: a rotating shaft; an impeller which is fixed to the rotating shaft; and a casing by which the rotating shaft is supported in a rotatable manner and in which an introduction channel introducing fluid to the impeller is formed.
  • the introduction channel includes: a nozzle blade which guides fluid flowing into the impeller; and a support member which is provided in an upstream side of the nozzle blade and which supports wall surfaces of the introduction channel, wherein the wall surfaces are mutually opposed.
  • the support member has a wing shape in a cross-sectional view.
  • a radial gas expander includes: a rotating shaft; two sets of impeller groups which are configured of impellers fixed to the rotating shaft, and are symmetrically provided in an axial direction;
  • the rotating shaft is supported in a rotatable manner, and in which a first introduction channel which introduces fluid to an impeller group of a first set, and a second introduction channel which is provided to be adjacent to the first introduction channel and introduces the fluid discharged from the impeller group of the first set to an impeller group of a second set are formed.
  • the second introduction channel includes: a nozzle blade which guides fluid flowing into the impeller; and a support member which is provided in an upstream side of the nozzle blade and which supports wall surfaces of the second introduction channel, wherein the wall surfaces are mutually opposed, and the support member has a wing shape in a cross-sectional view.
  • a desired channel width can be secured in the first introduction channel and the second introduction channel. Moreover, even when a pressure difference between the fluid flowing into the first introduction channel and the fluid flowing into the second introduction channel is large, the deformation amounts of a center wall and the mutually opposing wall surfaces of the second introduction channel can be decreased due to the support member, and since the support member is formed in the wing shape in a cross-sectional view, the flow of the fluid flowing into the nozzle blade can be prevented from being disturbed.
  • a plurality of the support members are provided around the rotating shaft, and a width of the support member is formed to be gradually narrowed from an outer circumferential in a radial direction toward an inner circumferential so that clearances between the support members are equal in the radial direction.
  • the fluid passing through the vicinity of the support member can be smoothly introduced to the nozzle blade without an increase in flow rate of the fluid.
  • the casing includes a casing main body and a plurality of diaphragms which are built in the casing main body and are integrally connected.
  • the introduction channel is formed in the plurality of diaphragms.
  • the casing to which the nozzle blade and the support member formed in the wing shape are incorporated, can be easily assembled. Moreover, maintenance of an inner portion can be easily performed.
  • a radial gas expander which obtains desired performance and can decrease the deformation amount of the wall of the diaphragm configuring the casing, can be provided.
  • FIG. 1 is a cross-sectional view of a radial gas expander according to an embodiment of the present invention.
  • FIG. 2 is an enlarged view of a portion A of FIG. 1 .
  • FIG. 3 is a view when viewed from B of FIG. 2 .
  • FIG. 4 is a view showing a streamline of gas which flows around a support blade.
  • FIG. 5 is a cross-sectional view of a radial gas expander of the related art.
  • FIG. 6 is a view when viewed from C of FIG. 5 , and is a view showing a streamline of gas which flows around a spacer.
  • a radial gas expander 1 As shown in FIGS. 1 and 2 , a radial gas expander 1 according to the embodiment of the present invention includes a tubular casing 2 , a rotating shaft 3 which is supported to the casing 2 in a rotatable manner and extends in an axial direction of the casing 2 , and a plurality of impellers 4 which are fixed to the rotating shaft 3 .
  • the axial direction of the casing 2 coincides with the axial direction of the rotating shaft 3 .
  • the axial direction of the casing 2 and the axial direction of the rotating shaft 3 are simply referred to as the axial direction.
  • the radial gas expander 1 includes two sections to expand gas in the inner portion. That is, the radial gas expander 1 includes two gas expander sections 5 a and 5 b which are configured of a gas expander section 5 a which is disposed in a first side of the axial direction and a gas expander section 5 b which is disposed in a second side of the axial direction.
  • the radial gas expander 1 of the present embodiment has a configuration which obtains a rotating drive force by the gas introduced to the first gas expander section 5 a and further obtains a rotating drive force by introducing the expanded gas discharged from the first gas expander section 5 a to the second gas expander section 5 b.
  • the casing 2 includes a casing main body 6 and a diaphragm group 7 which is provided in the inner portion of the casing main body 6 .
  • the diaphragm group 7 is configured of eleven diaphragms 8 , 9 a, 9 b, 10 a, 10 b, 11 a, lib, 12 a, 12 b, 13 a, 13 b which are configured to be capable of being pulled off in the axial direction.
  • the first gas expander section 5 a includes the diaphragm 8 which is disposed in the center and the diaphragms 9 a, 10 a, 11 a, 12 a, and 13 a which are connected in a first side of the diaphragm 8 .
  • the second gas expander section 5 b includes the diaphragm 8 which is disposed in the center and the diaphragms 9 b, 10 b, 11 b, 12 b, and 13 b which are connected in a second side of the diaphragm 8 .
  • two gas expander sections 5 a and 5 b have the central diaphragm 8 as a common component.
  • a suction port 18 a for introducing the gas to the first gas expander section 5 a and a suction port 18 b for introducing the gas to the second gas expander section 5 b are formed in the casing main body 6 .
  • a discharge port 19 a for discharging the gas from the first gas expander section 5 a and a discharge port 19 b for discharging the gas from the second gas expander section 5 b are formed in the casing main body 6 .
  • discharge port 19 a of the first gas expander section 5 a and the suction port 18 b of the second gas expander section 5 b are connected by a gas pipe 22 .
  • the rotating shaft 3 is disposed to penetrate the center of the diaphragm group 7 . Both end portions of the rotating shaft 3 are supported to diaphragms 13 a and 13 b, which are end plates of each of two gas expander sections 5 a and 5 b, in a rotatable manner via bearings 15 . Moreover, dry gas seals 16 are provided in the inner circumferences of the diaphragms 13 a and 13 b which are positioned inside each bearing 15 .
  • the plurality of impellers 4 are fixed onto the rotating shaft 3 , and impellers 4 of four stages configuring the first gas expander section 5 a and impellers 4 of four stages configuring the second gas expander section 5 b are arranged so as to be opposite to each other.
  • each impeller 4 when the opening portion which opens toward the outer circumferential in the radial direction of the impeller 4 is set to an inlet port 41 and the opening portion which opens toward the axial direction is set to a discharge port 42 , the impellers 4 of four stages configuring the first gas expander section 5 a and the impellers 4 of four stages configuring the second gas expander section 5 b are disposed so that in which the inlet ports 41 are positioned at sides of the central diaphragm 8 .
  • the impellers 4 configuring the first gas expander section 5 a are disposed so that the discharge port 42 faces the first side of the axial direction
  • the impellers 4 configuring the second gas expander section 5 b are disposed so that the discharge port 42 faces the second side of the axial direction.
  • the sizes of the plurality of impellers 4 are different from one another. Specifically, the sizes of the plurality of impellers 4 are changed to adapt to an expansion stroke of the gas.
  • a first introduction channel 20 a and a second introduction channel 20 b which communicate with the suction ports 18 a and 18 b respectively are formed between the diaphragms 9 a and 9 b which are positioned in both sides of the central diaphragm 8 . That is, the first introduction channel 20 a of the first gas expander section 5 a is formed between a wall surface 81 of the first side of the central diaphragm 8 and a wall surface 91 of the second side of the diaphragm 9 a.
  • the second introduction channel 20 b of the second gas expander section 5 b is formed between a wall surface 82 of the second side of the central diaphragm 8 and a wall surface 92 of the first side of the diaphragm 9 b.
  • first introduction channel 20 a and the second introduction channel 20 b are disposed to be adjacent to each other via the central diaphragm 8 .
  • outlet channels 21 a and 21 b which communicate with the above-described discharge ports 19 a and 19 b respectively, are formed between the diaphragms 13 a and 13 b which are end plates and the diaphragms 12 a and 12 b adjacent to the diaphragms 13 a and 13 b.
  • the outlet channel 21 a of the first gas expander section 5 a communicates with the discharge port 19 a of the casing main body 6
  • the outlet channel 21 b of the second gas expander section 5 b communicates with the discharge port 19 b of the casing main body 6 .
  • a plurality of nozzle blades 24 which guide the inflow of the gas to the impellers 4 , are provided in the upstream sides of the impellers 4 in each of the first introduction channel 20 a and the second introduction channel 20 b. In the present embodiment, 17 nozzle blades 24 are provided.
  • the nozzle blades 24 are disposed at equal intervals in the circumferential direction.
  • Each nozzle blade 24 has a wing shape in which a leading edge is round and a trailing edge is sharp in a cross-sectional shape when viewed in the axial direction.
  • the leading edges are disposed in the outer circumferential side of diaphragm in the circumferential direction
  • the trailing edges are disposed in the inner circumferential side of diaphragm in the circumferential direction
  • the nozzle blades 24 are disposed to be inclined in a rotating direction in a rotation direction R with respect to the leading edges so that the trailing edges are along the rotation direction R of the rotating shaft 3 . That is, front ends are disposed in the upstream in the flow direction of the gas, and rear ends are disposed in the downstream.
  • the cross-sectional shape of the nozzle blade 24 is determined using Computational Fluid Dynamic (CFD) analysis. Accordingly, the cross-sectional shape of the nozzle blade 24 of the present embodiment is formed to be asymmetrical with respect to a center line along the flow direction (hereinafter, referred to as a streamline direction) of the gas. That is, the nozzle blade 24 has a shape which smoothly introduces the flow of the gas to the impeller 4 to promote an operation which expands and accelerates the gas in the impeller 4 .
  • CFD Computational Fluid Dynamic
  • a plurality (seventeen sheets) of support blades 25 which are support members are provided in the further outer circumferential side of the nozzle blade 24 . Similar to the nozzle blades 24 , the support blades 25 are disposed at equal intervals in the circumferential direction.
  • Each support blade 25 has a so-called wing shape in which a leading edge is round and a trailing edge is sharp in a cross-sectional shape when viewed in the axial direction.
  • the leading edges are disposed in the outer circumferential side of diaphragm in the circumferential direction
  • the trailing edges are disposed in the inner circumferential sides of diaphragm in the circumferential direction
  • the support blades 25 are disposed to be inclined in the rotating direction in the rotation direction R with respect to the leading edges so that the trailing edges are along the rotation direction R. That is, in the support blades 25 , the front ends are disposed in the upstream in the streamline direction, and the rear ends are disposed in the downstream.
  • the shapes of the support blades 25 are formed so that a width of the support blade 25 is gradually narrowed from the outer circumferential in the radial direction toward the inner circumferential. Moreover, clearances W between the support blades 25 are approximately equal in the streamline direction, that is, the radial direction.
  • the cross-sectional shape of the support blade 25 is different from that of the nozzle blade 24 and is formed to be symmetrical with respect to the center line along the streamline direction.
  • the shape, the position in the circumferential direction, and the position in the radial direction of the support blade 25 are also determined using CFD or the like so as to influence the gas introduced to the nozzle blades 24 as little as possible, and particularly, it is preferable that the shape of the support blade has a shape along the streamline.
  • the length in the streamline direction be set within a range in which the influence to the streamline is small (which does not disturb the streamline) and be shortened as much as possible.
  • the streamline is changed according to a flow rate of the gas, it is preferable that the flow rate be appropriately determined according to the use conditions.
  • a return bend (intermediate channel) 27 having an U-shaped cross-section is formed which connects the discharge port 42 of the impeller 4 in the preceding stage and the inlet port 41 of the impeller 4 in the subsequent stage. Seventeen sheets of return vanes 28 are provided in the return bend 27 so that the gas flow to the nozzle blade 24 positioned in the upstream side of the impeller 4 and the inlet port 41 of the impeller 4 in the subsequent stage is efficient.
  • the gas having high temperature and high pressure is introduced to the first gas expander section 5 a via the suction port 18 a from a predetermined plant.
  • the suction and expansion are repeated over four stages by the impellers 4 of four stages, and the gas is discharged from the discharge port 19 a.
  • the gas is introduced to the second gas expander section 5 b via the gas pipe 22 and the suction port 18 b, is expanded in the second gas expander section 5 b, and is discharged from the discharge port 19 b.
  • the inflow gas flows in the axial direction in the inner portion of two gas expander sections 5 a and 5 b.
  • the gas flows in the directions opposite to each other. That is, the gas flows from the second side of the axial direction to the first side of the axial direction in the gas expander section 5 a. Moreover, the gas flows from the first side of the axial direction to the second side of the axial direction in the gas expander section 5 b.
  • the pressure of the gas which is introduced to the second introduction channel 20 b via the suction port 18 b is low. That is, the pressure difference between the pressures in the first introduction channel 20 a and the second introduction channel 20 b which are adjacent to each other via the diaphragm 8 is increased.
  • the pressure difference between the pressure in the first introduction channel 20 a and the pressure in the second introduction channel 20 b is increased, and even when a force of a degree as to cause the deformation of the diaphragm 8 is applied to the central diaphragm 8 formed between the first introduction channel 20 a and the second introduction channel 20 b, deformation amount can be decreased by providing the support blades 25 .
  • the support blade 25 is formed in the wing shape in a cross-sectional view, and thus, as shown in FIG. 4 , disturbance of the streamline L of the gas flowing around the support blades 25 can be decreased.
  • the shapes of the support blades 25 are formed so that a width of the support blade 25 is gradually narrowed from the outer circumferential in the radial direction toward the inner circumferential. Moreover, clearances W between the support blades 25 are equal in the radial direction. As a result, the gas passing through the vicinities of the support blades 25 can be smoothly introduced to the nozzle blade 24 without requiring an increase in flow rate of the gas.
  • the support blade 25 has the shape which is symmetrical in the streamline direction, the support blades can be more easily manufactured.
  • the plurality of diaphragm groups 7 configuring the casing 2 can be divided in the axial direction, maintenance in the inner portion can be easily performed.
  • the support blade 25 may have an asymmetrical shape in the streamline direction.
  • the radial gas expander of the present invention desired performance is obtained and the deformation amount of the wall of the diaphragm configuring the casing can be decreased.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Measuring Volume Flow (AREA)

Abstract

This radial gas expander is provided with a rotating shaft, an impeller which is fixed to the rotating shaft, and a casing by which the rotating shaft is supported in a rotatable manner and in which an introduction channel introducing fluid to the impeller is formed. The introduction channel includes a nozzle blade which guides fluid flowing into the impeller and a support member which is provided in the upstream side of the nozzle blade and which supports wall surfaces of the introduction channel, wherein the wall surfaces are mutually opposed, and the support member has a wing shape in a cross-sectional view.

Description

    TECHNICAL FIELD
  • The present invention relates to a radial gas expander (a radial flow gas expander) in which impellers are arranged on a single shaft in multiple stages.
  • Priority is claimed on Japanese Patent Application No. 2011-190525, filed Sep. 1, 2011, the content of which is incorporated herein by reference.
    • BACKGROUND ART
  • The gas expander is used to suction and expand high pressure gas discharged from a plant, convert pressure energy of the gas into speed energy (mechanical energy), and thus, recover power and reduce the power of a driving motor or the like.
  • In recent years, a gas expander which corresponds to higher pressure energy has been required. As such a gas expander, a radial gas expander in which a plurality of impellers is provided in multiple stages is known. As an example of the radial gas expander, a geared (speed-increasing gear) radial gas expander is known, which is configured of a driving gear, a speed-increasing gear configured of a pinion gear engaging with the driving gear, and a plurality of impellers disposed in a pinion shaft (for example, refer to Patent Document 1).
  • Moreover, a radial gas expander is also known in which the plurality of impellers are arranged between bearings on a single shaft and the impellers are built in a single casing. In the radial gas expander in which the plurality of impellers are arranged on the single shaft, the shaft is the single shaft in spite of including the multistage impeller. Accordingly, compared to the geared radial gas expander or the like, the number of high-pressure seals or high-pressure casing can be reduced to a minimum, and a radial gas expander having high reliability can be realized even in a higher pressure condition (for example, refer to Patent Document 2).
  • As shown in FIGS. 5 and 6, a radial gas expander 101 of the related art includes a casing 2, a rotating shaft 3 which is rotatably provided in the casing 2, and a plurality of impellers 4 which are fixed to the rotating shaft 3.
  • The radial gas expander 101 includes two gas expander sections 105 a and 105 b to expand the gas in the inner portion of the gas expander. The casing 2 is configured of a casing main body 6 and a diaphragm group 7 including a plurality of diaphragms which are built in the casing main body 6 and integrally connected. The gas expander sections 105 a and 105 b are configured to connect a plurality of diaphragms 8, 9 a, 9 b, 10 a, 10 b, 11 a, 11 b, 12 a, 12 b, 13 a, and 13 b, in which return bends connecting stages are formed, in an axial direction.
  • The expander section 105 a and 105 b includes gas introduction channels 120 a and 120 b communicating with suction ports 18 a and 18 b of the casing 2 and gas outflow channels 21 a and 21 b communicating with discharge ports 19 a and 19 b of the casing 2 in each section.
  • Among these, the gas introduction channels 120 a and 120 b are defined between the center diaphragm 8 which is provided in the center between two gas expander sections 105 a and 105 b and diaphragms 9 a and 9 b which are nearest to the center among the plurality of diaphragms except for the center diaphragm 8.
  • Nozzle blades 24, which generate a gas flow corresponding to profiles of the impellers 4, are provided in the upstream side of the impellers 4 on the gas introduction channel 120.
  • In the radial gas expander 101 having the above-described configuration, after the gas introduced via the suction port 18 a from a plant (not shown) is expanded in one gas expander section 105 a, the gas is introduced to the other gas expander section 105 b via gas pipes 22 and the suction port 18 b and is further expanded.
  • However, in the radial gas expander 101 of the related art, in order to secure channel widths of the gas introduction channel 120 a and the gas introduction channel 120 b, spacers 125 are installed in the upstream sides of the nozzle blades 24 of the gas introduction channels 120 a and 120 b.
    • RELATED ART DOCUMENTS Patent Document
  • [Patent Document 1] Japanese Patent No. 3457828
  • [Patent Document 2] Japanese Unexamined Patent Application, First Publication No. 2011-43070
    • SUMMARY OF THE INVENTION Problems to be Solved by the Invention
  • However, since the spacers 125 are installed in the upstream sides of the nozzle blades 24, there is a problem that a flow of the gas flowing into the nozzle blades 24 is disturbed. As shown in FIG. 6, when a streamline L of the introduced gas is disturbed by the spacers 125, loss occurs when the gas flows into the nozzle blades 24. Moreover, since the spacers are installed in the vicinity of inlets of the gas introduction channels 120 a and 120 b, reduction effects of an introduction channel width change are decreased due to differential pressure. Accordingly, a gas flow rate is changed according to the change of the channel width, a desired gas flow rate is not generated when the gas flows into the nozzle blades 24, and loss occurs. In this way, the spacers 125 impede expansion performance of the impellers 4, and furthermore, a decrease in the performance of the radial gas expander 101 occurs.
  • The present invention is made in consideration of the above-described circumstances, and an object thereof is to provide a radial gas expander capable of obtaining a desired performance. Moreover, an object thereof is to provide a radial gas expander capable of securing the channel widths of the gas introduction channels 120 a and 120 b and preventing walls of diaphragms configuring the casing from being deformed.
    • Means for Solving the Problems
  • In order to achieve the above-described objects, the present invention provides the following means.
  • According to a first aspect of the present invention, a radial gas expander includes: a rotating shaft; an impeller which is fixed to the rotating shaft; and a casing by which the rotating shaft is supported in a rotatable manner and in which an introduction channel introducing fluid to the impeller is formed. Moreover, the introduction channel includes: a nozzle blade which guides fluid flowing into the impeller; and a support member which is provided in an upstream side of the nozzle blade and which supports wall surfaces of the introduction channel, wherein the wall surfaces are mutually opposed. In addition, the support member has a wing shape in a cross-sectional view.
  • According to this configuration, distances from lower ends of the mutually opposing wall surfaces of the introduction channel provided in the casing to supporting points are shortened due to the support member, a deformation amount of the opposing wall surfaces can be decreased, and a desired channel width can be secured. Moreover, since the support member is formed in the wing shape in a cross-sectional view, the flow of the fluid flowing into the nozzle blade can be prevented from being disturbed.
  • Moreover, according to a second aspect of the present invention, a radial gas expander includes: a rotating shaft; two sets of impeller groups which are configured of impellers fixed to the rotating shaft, and are symmetrically provided in an axial direction;
  • and a casing by which the rotating shaft is supported in a rotatable manner, and in which a first introduction channel which introduces fluid to an impeller group of a first set, and a second introduction channel which is provided to be adjacent to the first introduction channel and introduces the fluid discharged from the impeller group of the first set to an impeller group of a second set are formed. Moreover, the second introduction channel includes: a nozzle blade which guides fluid flowing into the impeller; and a support member which is provided in an upstream side of the nozzle blade and which supports wall surfaces of the second introduction channel, wherein the wall surfaces are mutually opposed, and the support member has a wing shape in a cross-sectional view.
  • According to this configuration, a desired channel width can be secured in the first introduction channel and the second introduction channel. Moreover, even when a pressure difference between the fluid flowing into the first introduction channel and the fluid flowing into the second introduction channel is large, the deformation amounts of a center wall and the mutually opposing wall surfaces of the second introduction channel can be decreased due to the support member, and since the support member is formed in the wing shape in a cross-sectional view, the flow of the fluid flowing into the nozzle blade can be prevented from being disturbed.
  • According to a third aspect of the present invention, a plurality of the support members are provided around the rotating shaft, and a width of the support member is formed to be gradually narrowed from an outer circumferential in a radial direction toward an inner circumferential so that clearances between the support members are equal in the radial direction.
  • According to this configuration, the fluid passing through the vicinity of the support member can be smoothly introduced to the nozzle blade without an increase in flow rate of the fluid.
  • Moreover, according to a fourth aspect of the present invention, the casing includes a casing main body and a plurality of diaphragms which are built in the casing main body and are integrally connected. The introduction channel is formed in the plurality of diaphragms.
  • According to this configuration, the casing, to which the nozzle blade and the support member formed in the wing shape are incorporated, can be easily assembled. Moreover, maintenance of an inner portion can be easily performed.
    • Effect of the Invention
  • According to the present invention, a radial gas expander, which obtains desired performance and can decrease the deformation amount of the wall of the diaphragm configuring the casing, can be provided.
    • BRIEF DESCRIPTION OF DRAWINGS
  • FIG. 1 is a cross-sectional view of a radial gas expander according to an embodiment of the present invention.
  • FIG. 2 is an enlarged view of a portion A of FIG. 1.
  • FIG. 3 is a view when viewed from B of FIG. 2.
  • FIG. 4 is a view showing a streamline of gas which flows around a support blade.
  • FIG. 5 is a cross-sectional view of a radial gas expander of the related art.
  • FIG. 6 is a view when viewed from C of FIG. 5, and is a view showing a streamline of gas which flows around a spacer.
    •  DESCRIPTION OF EMBODIMENTS
  • An embodiment of the present invention will be described in detail with reference to the drawings.
  • As shown in FIGS. 1 and 2, a radial gas expander 1 according to the embodiment of the present invention includes a tubular casing 2, a rotating shaft 3 which is supported to the casing 2 in a rotatable manner and extends in an axial direction of the casing 2, and a plurality of impellers 4 which are fixed to the rotating shaft 3.
  • Moreover, in descriptions below, the axial direction of the casing 2 coincides with the axial direction of the rotating shaft 3. Moreover, the axial direction of the casing 2 and the axial direction of the rotating shaft 3 are simply referred to as the axial direction.
  • The radial gas expander 1 includes two sections to expand gas in the inner portion. That is, the radial gas expander 1 includes two gas expander sections 5 a and 5 b which are configured of a gas expander section 5 a which is disposed in a first side of the axial direction and a gas expander section 5 b which is disposed in a second side of the axial direction.
  • The radial gas expander 1 of the present embodiment has a configuration which obtains a rotating drive force by the gas introduced to the first gas expander section 5 a and further obtains a rotating drive force by introducing the expanded gas discharged from the first gas expander section 5 a to the second gas expander section 5 b.
  • The casing 2 includes a casing main body 6 and a diaphragm group 7 which is provided in the inner portion of the casing main body 6. The diaphragm group 7 is configured of eleven diaphragms 8, 9 a, 9 b, 10 a, 10 b, 11 a, lib, 12 a, 12 b, 13 a, 13 b which are configured to be capable of being pulled off in the axial direction.
  • The first gas expander section 5 a includes the diaphragm 8 which is disposed in the center and the diaphragms 9 a, 10 a, 11 a, 12 a, and 13 a which are connected in a first side of the diaphragm 8. Moreover, the second gas expander section 5 b includes the diaphragm 8 which is disposed in the center and the diaphragms 9 b, 10 b, 11 b, 12 b, and 13 b which are connected in a second side of the diaphragm 8.
  • That is, two gas expander sections 5 a and 5 b have the central diaphragm 8 as a common component.
  • A suction port 18 a for introducing the gas to the first gas expander section 5 a and a suction port 18 b for introducing the gas to the second gas expander section 5 b are formed in the casing main body 6.
  • Moreover, a discharge port 19 a for discharging the gas from the first gas expander section 5 a and a discharge port 19 b for discharging the gas from the second gas expander section 5 b are formed in the casing main body 6.
  • In addition, the discharge port 19 a of the first gas expander section 5 a and the suction port 18 b of the second gas expander section 5 b are connected by a gas pipe 22.
  • The rotating shaft 3 is disposed to penetrate the center of the diaphragm group 7. Both end portions of the rotating shaft 3 are supported to diaphragms 13 a and 13 b, which are end plates of each of two gas expander sections 5 a and 5 b, in a rotatable manner via bearings 15. Moreover, dry gas seals 16 are provided in the inner circumferences of the diaphragms 13 a and 13 b which are positioned inside each bearing 15.
  • The plurality of impellers 4 are fixed onto the rotating shaft 3, and impellers 4 of four stages configuring the first gas expander section 5 a and impellers 4 of four stages configuring the second gas expander section 5 b are arranged so as to be opposite to each other.
  • In each impeller 4, when the opening portion which opens toward the outer circumferential in the radial direction of the impeller 4 is set to an inlet port 41 and the opening portion which opens toward the axial direction is set to a discharge port 42, the impellers 4 of four stages configuring the first gas expander section 5 a and the impellers 4 of four stages configuring the second gas expander section 5 b are disposed so that in which the inlet ports 41 are positioned at sides of the central diaphragm 8. That is, the impellers 4 configuring the first gas expander section 5 a are disposed so that the discharge port 42 faces the first side of the axial direction, and the impellers 4 configuring the second gas expander section 5 b are disposed so that the discharge port 42 faces the second side of the axial direction.
  • Moreover, although the same reference numerals are attached to the plurality of impellers 4, the sizes of the plurality of impellers 4 are different from one another. Specifically, the sizes of the plurality of impellers 4 are changed to adapt to an expansion stroke of the gas.
  • A first introduction channel 20 a and a second introduction channel 20 b which communicate with the suction ports 18 a and 18 b respectively are formed between the diaphragms 9 a and 9 b which are positioned in both sides of the central diaphragm 8. That is, the first introduction channel 20 a of the first gas expander section 5 a is formed between a wall surface 81 of the first side of the central diaphragm 8 and a wall surface 91 of the second side of the diaphragm 9 a. Moreover, the second introduction channel 20 b of the second gas expander section 5 b is formed between a wall surface 82 of the second side of the central diaphragm 8 and a wall surface 92 of the first side of the diaphragm 9 b.
  • Accordingly, the first introduction channel 20 a and the second introduction channel 20 b are disposed to be adjacent to each other via the central diaphragm 8.
  • Similarly, outlet channels 21 a and 21 b, which communicate with the above-described discharge ports 19 a and 19 b respectively, are formed between the diaphragms 13 a and 13 b which are end plates and the diaphragms 12 a and 12 b adjacent to the diaphragms 13 a and 13 b.
  • Among these, the outlet channel 21 a of the first gas expander section 5 a communicates with the discharge port 19 a of the casing main body 6, and the outlet channel 21 b of the second gas expander section 5 b communicates with the discharge port 19 b of the casing main body 6.
  • A plurality of nozzle blades 24, which guide the inflow of the gas to the impellers 4, are provided in the upstream sides of the impellers 4 in each of the first introduction channel 20 a and the second introduction channel 20 b. In the present embodiment, 17 nozzle blades 24 are provided.
  • As shown in FIG. 3, the nozzle blades 24 are disposed at equal intervals in the circumferential direction. Each nozzle blade 24 has a wing shape in which a leading edge is round and a trailing edge is sharp in a cross-sectional shape when viewed in the axial direction. Moreover, in the nozzle blades 24, the leading edges are disposed in the outer circumferential side of diaphragm in the circumferential direction, the trailing edges are disposed in the inner circumferential side of diaphragm in the circumferential direction, and the nozzle blades 24 are disposed to be inclined in a rotating direction in a rotation direction R with respect to the leading edges so that the trailing edges are along the rotation direction R of the rotating shaft 3. That is, front ends are disposed in the upstream in the flow direction of the gas, and rear ends are disposed in the downstream.
  • In addition, for example, the cross-sectional shape of the nozzle blade 24 is determined using Computational Fluid Dynamic (CFD) analysis. Accordingly, the cross-sectional shape of the nozzle blade 24 of the present embodiment is formed to be asymmetrical with respect to a center line along the flow direction (hereinafter, referred to as a streamline direction) of the gas. That is, the nozzle blade 24 has a shape which smoothly introduces the flow of the gas to the impeller 4 to promote an operation which expands and accelerates the gas in the impeller 4.
  • A plurality (seventeen sheets) of support blades 25 which are support members are provided in the further outer circumferential side of the nozzle blade 24. Similar to the nozzle blades 24, the support blades 25 are disposed at equal intervals in the circumferential direction. Each support blade 25 has a so-called wing shape in which a leading edge is round and a trailing edge is sharp in a cross-sectional shape when viewed in the axial direction. Moreover, in the support blades 25, the leading edges are disposed in the outer circumferential side of diaphragm in the circumferential direction, the trailing edges are disposed in the inner circumferential sides of diaphragm in the circumferential direction, and the support blades 25 are disposed to be inclined in the rotating direction in the rotation direction R with respect to the leading edges so that the trailing edges are along the rotation direction R. That is, in the support blades 25, the front ends are disposed in the upstream in the streamline direction, and the rear ends are disposed in the downstream.
  • Moreover, the shapes of the support blades 25 are formed so that a width of the support blade 25 is gradually narrowed from the outer circumferential in the radial direction toward the inner circumferential. Moreover, clearances W between the support blades 25 are approximately equal in the streamline direction, that is, the radial direction.
  • In addition, the cross-sectional shape of the support blade 25 is different from that of the nozzle blade 24 and is formed to be symmetrical with respect to the center line along the streamline direction. The shape, the position in the circumferential direction, and the position in the radial direction of the support blade 25 are also determined using CFD or the like so as to influence the gas introduced to the nozzle blades 24 as little as possible, and particularly, it is preferable that the shape of the support blade has a shape along the streamline. Moreover, it is preferable that the length in the streamline direction be set within a range in which the influence to the streamline is small (which does not disturb the streamline) and be shortened as much as possible. In addition, since the streamline is changed according to a flow rate of the gas, it is preferable that the flow rate be appropriately determined according to the use conditions.
  • In the intermediate diaphragms 9 a, 10 a, 11 a, 12 a, 9 b, 10 b, 11 b, and 12 b in each of the gas expander sections 5 a and 5 b, a return bend (intermediate channel) 27 having an U-shaped cross-section is formed which connects the discharge port 42 of the impeller 4 in the preceding stage and the inlet port 41 of the impeller 4 in the subsequent stage. Seventeen sheets of return vanes 28 are provided in the return bend 27 so that the gas flow to the nozzle blade 24 positioned in the upstream side of the impeller 4 and the inlet port 41 of the impeller 4 in the subsequent stage is efficient.
  • An operation of the radial gas expander 1 having the above-described configuration will be described. First, the gas having high temperature and high pressure is introduced to the first gas expander section 5 a via the suction port 18 a from a predetermined plant. In the first gas expander section 5 a, the suction and expansion are repeated over four stages by the impellers 4 of four stages, and the gas is discharged from the discharge port 19 a. Subsequently, the gas is introduced to the second gas expander section 5 b via the gas pipe 22 and the suction port 18 b, is expanded in the second gas expander section 5 b, and is discharged from the discharge port 19 b.
  • The inflow gas flows in the axial direction in the inner portion of two gas expander sections 5 a and 5 b. However, according to the above-described configuration, the gas flows in the directions opposite to each other. That is, the gas flows from the second side of the axial direction to the first side of the axial direction in the gas expander section 5 a. Moreover, the gas flows from the first side of the axial direction to the second side of the axial direction in the gas expander section 5 b.
  • Here, compared to the pressure of the gas which is introduced to the first introduction channel 20 a via the suction port 18 a, the pressure of the gas which is introduced to the second introduction channel 20 b via the suction port 18 b is low. That is, the pressure difference between the pressures in the first introduction channel 20 a and the second introduction channel 20 b which are adjacent to each other via the diaphragm 8 is increased.
  • According to the above-described embodiment, the pressure difference between the pressure in the first introduction channel 20 a and the pressure in the second introduction channel 20 b is increased, and even when a force of a degree as to cause the deformation of the diaphragm 8 is applied to the central diaphragm 8 formed between the first introduction channel 20 a and the second introduction channel 20 b, deformation amount can be decreased by providing the support blades 25. Moreover, the support blade 25 is formed in the wing shape in a cross-sectional view, and thus, as shown in FIG. 4, disturbance of the streamline L of the gas flowing around the support blades 25 can be decreased.
  • Moreover, the shapes of the support blades 25 are formed so that a width of the support blade 25 is gradually narrowed from the outer circumferential in the radial direction toward the inner circumferential. Moreover, clearances W between the support blades 25 are equal in the radial direction. As a result, the gas passing through the vicinities of the support blades 25 can be smoothly introduced to the nozzle blade 24 without requiring an increase in flow rate of the gas.
  • In addition, since the support blade 25 has the shape which is symmetrical in the streamline direction, the support blades can be more easily manufactured.
  • Moreover, since the plurality of diaphragm groups 7 configuring the casing 2 can be divided in the axial direction, maintenance in the inner portion can be easily performed.
  • In addition, the technical scope of the present invention is not limited to the above-described embodiments, and various modifications can be applied within a scope which does not depart from the gist of the present invention. For example, the support blade 25 may have an asymmetrical shape in the streamline direction.
    • INDUSTRIAL APPLICABILITY
  • According to the radial gas expander of the present invention, desired performance is obtained and the deformation amount of the wall of the diaphragm configuring the casing can be decreased.
    • DESCRIPTION OF REFERENCE NUMERALS
    • 1: radial gas expander
    • 2: casing
    • 3: rotating shaft
    • 4: impeller
    • 5: gas expander section
    • 6: casing main body
    • 7: diaphragm group
    • 8, 9 a, 9 b, 10 a, 10 b, 11 a, 11 b, 12 a, 12 b, 13 a, and 13 b: diaphragm
    • 20 a: first introduction channel (introduction channel)
    • 20 b: second introduction channel (introduction channel)
    • 24: nozzle blade
    • 25: support blade (support member)
    • 27: return bend

Claims (8)

1. A radial gas expander comprising:
a rotating shaft;
an impeller which is fixed to the rotating shaft; and
a casing by which the rotating shaft is supported in a rotatable manner and in which an introduction channel introducing fluid to the impeller is formed,
wherein the introduction channel includes:
a nozzle blade which guides fluid flowing into the impeller; and
a support member which is provided in an upstream side of the nozzle blade and which supports wall surfaces of the introduction channel, wherein the wall surfaces are mutually opposed, and
wherein the support member has a wing shape in a cross-sectional view.
2. A radial gas expander comprising:
a rotating shaft;
two sets of impeller groups which are configured of impellers fixed to the rotating shaft, and are symmetrically provided in an axial direction; and
a casing by which the rotating shaft is supported in a rotatable manner, and in which a first introduction channel which introduces fluid to an impeller group of a first set, and a second introduction channel which is provided to be adjacent to the first introduction channel and introduces the fluid discharged from the impeller group of the first set to an impeller group of a second set are formed,
wherein the second introduction channel includes:
a nozzle blade which guides fluid flowing into the impeller; and
a support member which is provided in an upstream side of the nozzle blade and which supports wall surfaces of the second introduction channel, wherein the wall surfaces are mutually opposed, and
wherein the support member has a wing shape in a cross-sectional view.
3. The radial gas expander according to claim 1,
wherein a plurality of the support members are provided around the rotating shaft, and a width of the support member is formed to be gradually narrowed from an outer circumferential in a radial direction toward an inner circumferential so that clearances between the support members are equal in the radial direction.
4. The radial gas expander according to claim 1,
wherein the casing includes a casing main body and a plurality of diaphragms which are built in the casing main body and are integrally connected, and
wherein the introduction channel is formed between the diaphragms.
5. The radial gas expander according to claim 2,
wherein a plurality of the support members are provided around the rotating shaft, and a width of the support member is formed to be gradually narrowed from an outer circumferential in a radial direction toward an inner circumferential so that clearances between the support members are equal in the radial direction.
6. The radial gas expander according to claim 2,
wherein the casing includes a casing main body and a plurality of diaphragms which are built in the casing main body and are integrally connected, and
wherein the introduction channel is formed between the diaphragms.
7. The radial gas expander according to claim 3,
wherein the casing includes a casing main body and a plurality of diaphragms which are built in the casing main body and are integrally connected, and
wherein the introduction channel is formed between the diaphragms.
8. The radial gas expander according to claim 5,
wherein the casing includes a casing main body and a plurality of diaphragms which are built in the casing main body and are integrally connected, and
wherein the introduction channel is formed between the diaphragms.
US14/125,990 2011-09-01 2012-01-06 Radial gas expander Abandoned US20140126994A1 (en)

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PCT/JP2012/050165 WO2013031244A1 (en) 2011-09-01 2012-01-06 Radial gas expander

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT201800002047A1 (en) * 2018-01-26 2019-07-26 Nuovo Pignone Tecnologie Srl A MULTI-STAGE RADIAL TURBOEXPANT
US11560903B2 (en) 2020-02-03 2023-01-24 Mitsubishi Heavy Industries Compressor Corporation Rotary machine
CN119412165A (en) * 2024-10-30 2025-02-11 西安交通大学 A centrifugal expander

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105324554B (en) * 2013-06-28 2017-05-24 三菱重工压缩机有限公司 axial flow expander
WO2014210409A1 (en) 2013-06-28 2014-12-31 Exxonmobil Upstream Research Company Systems and methods of utilizing axial flow expanders
CN103993914A (en) * 2014-05-23 2014-08-20 马鞍山市晨光高耐磨科技发展有限公司 Stator steam inlet structure of run-off type steam turbine
WO2016127731A1 (en) * 2015-02-15 2016-08-18 靳北彪 Inter-pressure impeller mechanism
WO2021140569A1 (en) 2020-01-07 2021-07-15 三菱重工エンジン＆ターボチャージャ株式会社 Turbine and turbocharger
CN112377269B (en) * 2021-01-11 2021-03-26 中国空气动力研究与发展中心高速空气动力研究所 Anti-distortion stator design method suitable for contra-rotating lift propulsion device

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3369737A (en) * 1962-12-10 1968-02-20 Gen Electric Radial flow machine
US4186557A (en) * 1978-05-22 1980-02-05 Toyota Jidosha Kogyo Kabushiki Kaisha Torque converter with narrowed flow passages
JPH0315666A (en) * 1989-06-12 1991-01-24 Hitachi Ltd water wheel
US5562405A (en) * 1994-03-10 1996-10-08 Weir Pumps Limited Multistage axial flow pumps and compressors
US7001143B2 (en) * 2002-09-05 2006-02-21 Honeywell International, Inc. Cambered vane for use in turbochargers
US7396204B2 (en) * 2002-10-18 2008-07-08 Mitshubishi Heavy Industries, Ltd. Variable-nozzle mechanism, exhaust turbocharger equipped therewith, and method of manufacturing exhaust turbocharger with the variable-nozzle mechanism
US20110123316A1 (en) * 2008-07-25 2011-05-26 Roberts Tom J Variable geometry turbine
US8056336B2 (en) * 2008-05-05 2011-11-15 Honeywell International Inc. Turbocharger with variable nozzle having vane sealing surfaces
US8596955B2 (en) * 2006-07-26 2013-12-03 Peter Brotherhood Limited Impulse turbine for use in bi-directional flows
US8985945B2 (en) * 2009-08-19 2015-03-24 Mitsubishi Heavy Industries Compressor Corporation Radial gas expander

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2034817B (en) * 1978-11-20 1982-12-08 Plessey Co Ltd Centrifugal pump
JPS6050962B2 (en) * 1978-12-04 1985-11-11 株式会社日立製作所 radial turbine
JPS63147903A (en) * 1986-12-09 1988-06-20 Isuzu Motors Ltd Turbine casing structure
JPS63201326A (en) * 1987-02-16 1988-08-19 Juichi Unno Gas turbine
JPH053684Y2 (en) * 1987-10-26 1993-01-28
US7632073B2 (en) * 2005-06-08 2009-12-15 Dresser-Rand Company Impeller with machining access panel
JP4812597B2 (en) * 2006-11-09 2011-11-09 トヨタ自動車株式会社 Turbocharger
WO2008090628A1 (en) * 2007-01-26 2008-07-31 Hitachi, Ltd. Steam turbine type power generating apparatus and method of operating the same

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3369737A (en) * 1962-12-10 1968-02-20 Gen Electric Radial flow machine
US4186557A (en) * 1978-05-22 1980-02-05 Toyota Jidosha Kogyo Kabushiki Kaisha Torque converter with narrowed flow passages
JPH0315666A (en) * 1989-06-12 1991-01-24 Hitachi Ltd water wheel
US5562405A (en) * 1994-03-10 1996-10-08 Weir Pumps Limited Multistage axial flow pumps and compressors
US7001143B2 (en) * 2002-09-05 2006-02-21 Honeywell International, Inc. Cambered vane for use in turbochargers
US7396204B2 (en) * 2002-10-18 2008-07-08 Mitshubishi Heavy Industries, Ltd. Variable-nozzle mechanism, exhaust turbocharger equipped therewith, and method of manufacturing exhaust turbocharger with the variable-nozzle mechanism
US8596955B2 (en) * 2006-07-26 2013-12-03 Peter Brotherhood Limited Impulse turbine for use in bi-directional flows
US8056336B2 (en) * 2008-05-05 2011-11-15 Honeywell International Inc. Turbocharger with variable nozzle having vane sealing surfaces
US20110123316A1 (en) * 2008-07-25 2011-05-26 Roberts Tom J Variable geometry turbine
US8985945B2 (en) * 2009-08-19 2015-03-24 Mitsubishi Heavy Industries Compressor Corporation Radial gas expander

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Machine translation of JP 2008121470 A (29 May 2008) from Espacenet *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT201800002047A1 (en) * 2018-01-26 2019-07-26 Nuovo Pignone Tecnologie Srl A MULTI-STAGE RADIAL TURBOEXPANT
EP3517729A1 (en) * 2018-01-26 2019-07-31 Nuovo Pignone Technologie S.r.l. A multi-stage radial turboexpander
US10927756B2 (en) * 2018-01-26 2021-02-23 Nuovo Pignone Tecnologie Srl Multi-stage radial turboexpander
US11560903B2 (en) 2020-02-03 2023-01-24 Mitsubishi Heavy Industries Compressor Corporation Rotary machine
EP3859161B1 (en) * 2020-02-03 2025-10-08 Mitsubishi Heavy Industries Compressor Corporation Rotary machine
CN119412165A (en) * 2024-10-30 2025-02-11 西安交通大学 A centrifugal expander

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JP2013053530A (en) 2013-03-21
JP5959816B2 (en) 2016-08-02

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Owner name: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION

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Effective date: 20131209

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