US3236500A - Turbine - Google Patents

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Publication number
US3236500A
US3236500A US239035A US23903562A US3236500A US 3236500 A US3236500 A US 3236500A US 239035 A US239035 A US 239035A US 23903562 A US23903562 A US 23903562A US 3236500 A US3236500 A US 3236500A
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United States
Prior art keywords
rotor
periphery
casing
blades
turbine
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Expired - Lifetime
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US239035A
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Kofink Siegfried
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Geratebau Eberspacher OHG
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Geratebau Eberspacher OHG
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    • 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
    • F01D17/146—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by throttling the volute inlet of radial machines or engines
    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser

Definitions

  • This invention relates in general to turbine construction, and in particular to a new and useful gas turbine construction of a radial design having a casing wall with slots adjacent the periphery of rotor blades to permit insertion of covering plates for the blades for varying the amount of flow through the various blades.
  • a turbine having a housing defined as a spiral for the admission of the operating fluid and which includes a side wall for the housing having openings at a location adjacent the periphery of a rotor blade rotatable within the housing.
  • the openings are provided for receiving one or more covering elements which extend through the wall of the turbine and may be positioned to align with the periphery of the blades for the purpose of limiting the amount of flow through the blades.
  • the coverings are advantageously mounted on a control element such as a ring which may be moved in accordance with the operating characteristics of the turbine in order to provide the desired speed thereof.
  • the covers are such that they substantially fill the opening of a slot defined in the wall of a casing, and when they are moved to an inoperative position they cover said opening.
  • a further object of the invention is to provide a turbine construction including a housing having a wall with at least one Opening therein at a location adjacent the periphery of the rotor blade operating within the housing and including a covering element for the blades which is insertable in the opening.
  • a further object of the invention is to provide a turbine having a housing or casing constructed to provide spiral inflow of the driving fluid, and which includes a rotatable turbine wheel therein, the housing having a plurality of openings at locations spaced around the periphery of the rotatable blade, and including a control element having a plurality of covering members which are insertable in respective openings for the purpose of regulating fluid flow through the blades.
  • a further object of the invention is to provide a turbine which is simple in design, rugged in construction and economical to manufacture.
  • FIG. 1 is a partial elevational and partial fragmentary sectional view of a gas turbine constructed in accordance with the invention
  • FIG. 2 is a section taken on the line 2-2 of FIG. 1;
  • FIG, 3 is a view similar to FIG. 1 of another embodiment of the invention.
  • FIG. 4 is a section taken along the line 4-4 of FIG. 3.
  • FIGS. 1 and 2 a turbine generally designated 10 which includes a housing 1 which is of generally spiral configuration to provide for the spiral inflow of driving fluid such as exhaust gases from an internal combustion engine.
  • a central radial impeller 2 having blades 3 is rotatably mounted within the housing 1 on an axis or shaft 12.
  • the turbine casing 1 includes a wall or bulkhead 4 having a plurality of circumferentially spaced openings 14 located adjacent the periphery of the blades 3.
  • a control element or holding ring 5 is provided with a similar number of covering elements 6 which are of a size to be inserted within the openings 14.
  • the slots or openings 14 correspond in size and configuration to the size of the covering element 6.
  • the holding ring 5 is connected by an element 16 to means sensing the quantity of gas which is admitted through an opening 18 in the turbine casing.
  • the means which are located to sense the fluid admitted at the opening 18 actuate the member 16 to cause the holding ring 5 to move inwardly and insert the covering 6 within the casing 1 in a position to cover the blade elements 3, as indicated in the drawings. In this manner, they reduce the total passage cross section to the blade channels of the impeller 2.
  • the coverings 6 are advantageously shaped in the form of an airplane wing with the forward end rounded and the trailing end pointed, so that the flow in the direction of the arrows 20 will be aerodynamically stable and not inhibited.
  • a gas turbine 10' is provided with a casing 1' of a configuraiton similar to that indicated in the other embodiment.
  • a cylindrical formation 8 is provided at the periphery of the casing on the bulkhead or wall 4'.
  • a control member 7 is movable within the cylinder 8 in accordance with the flow conditions of the operating gas which enters in an opening 18 of the turbine.
  • the control member 7 is provided with finger elements or covers 7a which slide in a slot or opening 14 defined in the wall 4' adjacent the periphery of the blades 3'.
  • the covering elements are made in the form of segments of a cylinder. They are advantageously made slightly smaller than the spacing between the blades for the purpose of control of fluid flow therethrough.
  • a gas turbine comprising a casing having a side wall and Wall means for directing gas in a spiral, a rotor rotata-bly mounted within said casing with the periphery thereof defining a spiral with the outer wall of said casing, said rotor having a plurality of radially extending blades spaced angularly to define entrance openings at their peripheries, a plurality of openings defined in said side wall of said casing adjacent the periphery of said rotor at circumferentially spaced locations, and a control ring, a plurality of circumferentially spaced covering elements corresponding in number to the number of said .openings and forming a unitary structure with said ring,
  • said covering elements being located at circum-ferentially spaced locations around the periphery of said rotor and being circumferentially elongated sufliciently to cover the entrance openings between adjacent ones of said rotor blades and having an inner surface concentric to the axis of rotation of said rotor blades and having a leading and trailing edge, the outer surface between said edges being defined by an unbroken, smooth, continuously changing curved surface, said control means being axially movable in one direction to position said coverings within said casing adjacent the periphery of said blades for covering a portion of the periphery of said rotor between a plurality of blades for regulating the operating characteristics of said turbine and axially movable in an opposite direction to uncover the periphery of said rotor.
  • a device wherein said covering element is in the form of a segment of a circle in profile.
  • control means includes a piston member, said casing having a plurality of cylinders defined at locations surrounding each of said openings, said control element including a plurality of piston portions slidable in said cylinders.

Description

S. KOFINK TURBINE Feb. 22, 1966 2 Sheets-Sheet 1 Filed Nov. 20, 1962 InvenIor:
Feb. 22, 1966 s. KOFINK 3,236,500
TURBINE Filed Nov. 20,. 1962 2 Sheets-Sheet 2 United States Patent Ofilice 3,236,500 Patented Feb. 22, 1966 4 Claims. cl. 253-121 This invention relates in general to turbine construction, and in particular to a new and useful gas turbine construction of a radial design having a casing wall with slots adjacent the periphery of rotor blades to permit insertion of covering plates for the blades for varying the amount of flow through the various blades.
The present invention is related to applicants copending application Serial No. 147,356, filed October 24, 1961, now patent No, 3,137,477. In that application, certain means have been disclosed for adapting the impeller channels of fluid turbines to a regulation of fluid admission by employing coverings in a nozzle ring which are coordinated in a manner to provide constant speed operation regardless of the flow of the fluid to the turbine.
In accordance with the present invention, there is provided a turbine having a housing defined as a spiral for the admission of the operating fluid and which includes a side wall for the housing having openings at a location adjacent the periphery of a rotor blade rotatable within the housing. The openings are provided for receiving one or more covering elements which extend through the wall of the turbine and may be positioned to align with the periphery of the blades for the purpose of limiting the amount of flow through the blades. In accordance with the invention, the coverings are advantageously mounted on a control element such as a ring which may be moved in accordance with the operating characteristics of the turbine in order to provide the desired speed thereof. With the invention, it is a simple matter to either insert or remove the covering so that the operation of the turbine is aflected thereby. The covers are such that they substantially fill the opening of a slot defined in the wall of a casing, and when they are moved to an inoperative position they cover said opening.
Accordingly, it is an object of this invention to provide an improved turbine construction.
A further object of the invention is to provide a turbine construction including a housing having a wall with at least one Opening therein at a location adjacent the periphery of the rotor blade operating within the housing and including a covering element for the blades which is insertable in the opening.
A further object of the invention is to provide a turbine having a housing or casing constructed to provide spiral inflow of the driving fluid, and which includes a rotatable turbine wheel therein, the housing having a plurality of openings at locations spaced around the periphery of the rotatable blade, and including a control element having a plurality of covering members which are insertable in respective openings for the purpose of regulating fluid flow through the blades.
A further object of the invention is to provide a turbine which is simple in design, rugged in construction and economical to manufacture.
The various features of novelty which characterize the invention are pointed out with particularity in the claims annexed to and forming a part of this specification. For a better understanding of the invention, its operating advantages and specific objects attained by its use, reference should be had to the accompanying drawings and descriptive matter in which there are illustrated and described preferred embodiments of the invention.
In the drawings:
FIG. 1 is a partial elevational and partial fragmentary sectional view of a gas turbine constructed in accordance with the invention;
FIG. 2 is a section taken on the line 2-2 of FIG. 1;
FIG, 3 is a view similar to FIG. 1 of another embodiment of the invention; and
FIG. 4 is a section taken along the line 4-4 of FIG. 3.
Referring to the drawings in particular, the invention embodied therein includes in FIGS. 1 and 2 a turbine generally designated 10 which includes a housing 1 which is of generally spiral configuration to provide for the spiral inflow of driving fluid such as exhaust gases from an internal combustion engine. A central radial impeller 2 having blades 3 is rotatably mounted within the housing 1 on an axis or shaft 12.
In accordance with the invention, the turbine casing 1 includes a wall or bulkhead 4 having a plurality of circumferentially spaced openings 14 located adjacent the periphery of the blades 3. A control element or holding ring 5 is provided with a similar number of covering elements 6 which are of a size to be inserted within the openings 14. The slots or openings 14 correspond in size and configuration to the size of the covering element 6.
The holding ring 5 is connected by an element 16 to means sensing the quantity of gas which is admitted through an opening 18 in the turbine casing. The means which are located to sense the fluid admitted at the opening 18 actuate the member 16 to cause the holding ring 5 to move inwardly and insert the covering 6 within the casing 1 in a position to cover the blade elements 3, as indicated in the drawings. In this manner, they reduce the total passage cross section to the blade channels of the impeller 2. In the embodiment illustrated in FIGS. 1 and 2, the coverings 6 are advantageously shaped in the form of an airplane wing with the forward end rounded and the trailing end pointed, so that the flow in the direction of the arrows 20 will be aerodynamically stable and not inhibited.
As indicated in FIGS. 3 and 4, a gas turbine 10' is provided with a casing 1' of a configuraiton similar to that indicated in the other embodiment. In this embodiment, however, a cylindrical formation 8 is provided at the periphery of the casing on the bulkhead or wall 4'. A control member 7 is movable within the cylinder 8 in accordance with the flow conditions of the operating gas which enters in an opening 18 of the turbine. The control member 7 is provided with finger elements or covers 7a which slide in a slot or opening 14 defined in the wall 4' adjacent the periphery of the blades 3'. In this embodiment, the covering elements are made in the form of segments of a cylinder. They are advantageously made slightly smaller than the spacing between the blades for the purpose of control of fluid flow therethrough.
While specific embodiments of the invention have been shown and described in detail to illustrate the application of the invention principles, it will be understood that the invention may be embodied otherwise without departing from such principles.
What is claimed is:
1. A gas turbine comprising a casing having a side wall and Wall means for directing gas in a spiral, a rotor rotata-bly mounted within said casing with the periphery thereof defining a spiral with the outer wall of said casing, said rotor having a plurality of radially extending blades spaced angularly to define entrance openings at their peripheries, a plurality of openings defined in said side wall of said casing adjacent the periphery of said rotor at circumferentially spaced locations, and a control ring, a plurality of circumferentially spaced covering elements corresponding in number to the number of said .openings and forming a unitary structure with said ring,
said covering elements being located at circum-ferentially spaced locations around the periphery of said rotor and being circumferentially elongated sufliciently to cover the entrance openings between adjacent ones of said rotor blades and having an inner surface concentric to the axis of rotation of said rotor blades and having a leading and trailing edge, the outer surface between said edges being defined by an unbroken, smooth, continuously changing curved surface, said control means being axially movable in one direction to position said coverings within said casing adjacent the periphery of said blades for covering a portion of the periphery of said rotor between a plurality of blades for regulating the operating characteristics of said turbine and axially movable in an opposite direction to uncover the periphery of said rotor.
2. A device according to claim 1, wherein said covering element is substantially wing-shaped in profile.
3. A device according to claim 1, wherein said covering element is in the form of a segment of a circle in profile.
4. A gas turbine according to claim 1, wherein said control means includes a piston member, said casing having a plurality of cylinders defined at locations surrounding each of said openings, said control element including a plurality of piston portions slidable in said cylinders.
References Cited by the Examiner UNITED STATES PATENTS 268,287 l1/1882 Risdonet a1. 253-104 1,353,915 9/1920 Kime 10397 1,659,410 2/1928 Schmidt 103103 2,285,976 6/1942 Huitson 253-52 2,465,527 3/1949 Goddard 103-103 2,519,151 8/1950 Overweg 230114 2,770,943 11/1956 Beale 25355 FOREIGN PATENTS 875,086 6/1942 France.
848,330 9/ 1952 Germany.
305,214 1/1929 Great Britain.
738,987 10/1955 Great Britain.
750,635 6/1956 Great Britain.
753,316 7/1956 Great Britain.
133,892 6/ 1929 Switzerland.
DONLEY J. STOCKING, Primary Examiner.
25 LAURENCE V. EFNER, JOSEPH H. BRANSON, JR.,
KARL J. ALBRECHT, Examiners.

Claims (1)

1. A GAS TURBINE COMPRISING A CASING HAVING A SIDE WALL AND WALL MEANS FOR DIRECTING GAS IN A SPIRAL, A ROTOR ROTATABLY MOUNTED WITHIN SAID CASING WITH THE PERIPHERY THEREOF DEFINING A SPIRAL WITH THE OUTER WALL OF SAID CASING, SAID ROTOR HAVING A PLURALITY OF RADIALLY EXTENDING BLADES SPACED ANGULARLY TO DEFINE ENTRANCE OPENINGS AT THEIR PERIPHERIES, A PLURALITY OF OPENINGS DEFINED IN SAID SIDE WALL OF SAID CASING ADJACENT THE PERIPHERY OF SAID ROTOR AT CIRCUMFERENTIALLY SPACED LOCATIONS, AND A CONTROL RING, A PLURALITY OF CIRCUMFERENTAILLY SPACED COVERING ELEMENTS CORRESPONDING IN NUMBER TO THE NUMBER OF SAID OPENINGS AND FORMING A UNITARY STRUCTURE WITH SAID RING, SAID COVERING ELEMENTS BEING LOCATED AT CIRCUMFERENTIALLY SPACED LOCATIONS AROUND THE PERIPHERY OF SAID ROTOR AND BEING CIRCUMFERENTIALLY ELONGATED SUFFICIENTLY TO COVER THE ENTRANCE OPENINGS BETWEEN ADJACENT ONES OF SAID ROTOR BLADES AND HAVING AN INNER SURFACE CONCENTRIC TO THE AXIS OF ROTATION OF SAID ROTOR BLADES AND HAVING A LEADING AND TRAILING EDGE, THE OUTER SURFACE BETWEEN SAID EDGES BEING DEFINED BY AN UNBROKEN, SMOOTH, CONTINUOUSLY CHANGING CURVED SURFACE, SAID CONTROL MEANS BEING AXIALLY MOVABLE IN ONE DIRECTION TO POSITION SAID COVERINGS WITHIN SAID CASING ADJACNET THE PERIPHERY OF SAID ROTOR BETWEEN COVERING A PORTION OF THE PERIPHERY OF SAID ROTOR BETWEEN A PLURALITY OF BLADES FOR REGULATING THE OPERATING CHARACTERISTICS OF SAID TURBINE AND AXIALLY MOVABLE IN AN OPPOSITE DIRECTION TO UNCOVER THE PERIPHERY OF SAID ROTOR.
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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3433165A (en) * 1967-07-18 1969-03-18 Ckd Blansko Narodni Podnik Hydraulic apparatus
US3784318A (en) * 1971-12-29 1974-01-08 Gen Electric Variable diffuser centrifugal pump
US3826586A (en) * 1972-12-29 1974-07-30 Gen Electric Variable diffuser centrifugal pump shutter control
US3901624A (en) * 1973-12-10 1975-08-26 Allis Chalmers Integrated gate operating servomotor
US3941498A (en) * 1974-04-08 1976-03-02 Chandler Evans Inc. Variable geometry collector for centrifugal pump
DE2633587A1 (en) * 1976-07-27 1978-02-02 Kloeckner Humboldt Deutz Ag COMBUSTION ENGINE WITH EXHAUST GAS TURBOCHARGER
US4261685A (en) * 1978-03-31 1981-04-14 The Garrett Corp. Energy transfer machine
FR2524065A1 (en) * 1982-03-24 1983-09-30 Renault Turbocharger for IC-engine - has sliding gate to control exhaust gas inlet to turbine
EP0095853A1 (en) * 1982-05-28 1983-12-07 Holset Engineering Company Limited A variable inlet area turbine
WO1987006981A2 (en) * 1986-05-13 1987-11-19 Richard John Sauter Centrifugal superchargers
US20040105756A1 (en) * 2002-08-30 2004-06-03 Mitsubishi Heavy Industries, Ltd. Mixed flow turbine and mixed flow turbine rotor blade
US20130136590A1 (en) * 2011-01-27 2013-05-30 Hirotaka Higashimori Radial turbine
US20140328667A1 (en) * 2012-11-09 2014-11-06 Susan J. NENSTIEL Variable geometry diffuser having extended travel and control method thereof
US20150275917A1 (en) * 2014-03-26 2015-10-01 Kabushiki Kaisha Toyota Jidoshokki Centrifugal Compressor
US20160208808A1 (en) * 2013-08-26 2016-07-21 Gree Electric Appliances, Inc. Of Zhuhai Regulator assembly and centrifugal compressor

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US268287A (en) * 1882-11-28 Theodore h
US1353915A (en) * 1919-11-21 1920-09-28 Ransom R Micks Centrifugal-pump
US1659410A (en) * 1925-03-06 1928-02-14 Westinghouse Electric & Mfg Co Centrifugal pump
CH133892A (en) * 1928-07-18 1929-06-30 Sulzer Ag Centrifugal pump.
GB305214A (en) * 1928-02-02 1929-10-31 Rateau Soc Improvements in or relating to means for controlling the running of centrifugal machines
US2285976A (en) * 1940-01-15 1942-06-09 Gen Electric Centrifugal compressor
FR875086A (en) * 1940-01-13 1942-09-05 Deutsche Schiff & Maschb Ag Reversible centrifugal fan
US2465527A (en) * 1947-02-01 1949-03-29 Daniel And Florence Guggenheim Centrifugal pump with intermittent discharge
US2519151A (en) * 1944-08-16 1950-08-15 Machf Gebr Stork & Co N V Centrifugal fan or centrifugal pump for two directions of rotation
DE848330C (en) * 1948-10-29 1952-09-04 English Electric Co Ltd Water turbine
GB738987A (en) * 1951-12-05 1955-10-26 David Douglas Williamson Improvements in and relating to turbines having movable directive vanes
GB750635A (en) * 1953-12-11 1956-06-20 English Electric Co Ltd Improvements in and relating to hydraulic turbines and pumps
GB753316A (en) * 1953-04-24 1956-07-25 Power Jets Res & Dev Ltd Improvements relating to radial-flow turbines or compressors
US2770943A (en) * 1951-03-21 1956-11-20 Alan Muntz & Co Ltd Turbines operated by free-piston gas generators

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US268287A (en) * 1882-11-28 Theodore h
US1353915A (en) * 1919-11-21 1920-09-28 Ransom R Micks Centrifugal-pump
US1659410A (en) * 1925-03-06 1928-02-14 Westinghouse Electric & Mfg Co Centrifugal pump
GB305214A (en) * 1928-02-02 1929-10-31 Rateau Soc Improvements in or relating to means for controlling the running of centrifugal machines
CH133892A (en) * 1928-07-18 1929-06-30 Sulzer Ag Centrifugal pump.
FR875086A (en) * 1940-01-13 1942-09-05 Deutsche Schiff & Maschb Ag Reversible centrifugal fan
US2285976A (en) * 1940-01-15 1942-06-09 Gen Electric Centrifugal compressor
US2519151A (en) * 1944-08-16 1950-08-15 Machf Gebr Stork & Co N V Centrifugal fan or centrifugal pump for two directions of rotation
US2465527A (en) * 1947-02-01 1949-03-29 Daniel And Florence Guggenheim Centrifugal pump with intermittent discharge
DE848330C (en) * 1948-10-29 1952-09-04 English Electric Co Ltd Water turbine
US2770943A (en) * 1951-03-21 1956-11-20 Alan Muntz & Co Ltd Turbines operated by free-piston gas generators
GB738987A (en) * 1951-12-05 1955-10-26 David Douglas Williamson Improvements in and relating to turbines having movable directive vanes
GB753316A (en) * 1953-04-24 1956-07-25 Power Jets Res & Dev Ltd Improvements relating to radial-flow turbines or compressors
GB750635A (en) * 1953-12-11 1956-06-20 English Electric Co Ltd Improvements in and relating to hydraulic turbines and pumps

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3433165A (en) * 1967-07-18 1969-03-18 Ckd Blansko Narodni Podnik Hydraulic apparatus
US3784318A (en) * 1971-12-29 1974-01-08 Gen Electric Variable diffuser centrifugal pump
US3826586A (en) * 1972-12-29 1974-07-30 Gen Electric Variable diffuser centrifugal pump shutter control
US3901624A (en) * 1973-12-10 1975-08-26 Allis Chalmers Integrated gate operating servomotor
US3941498A (en) * 1974-04-08 1976-03-02 Chandler Evans Inc. Variable geometry collector for centrifugal pump
DE2633587A1 (en) * 1976-07-27 1978-02-02 Kloeckner Humboldt Deutz Ag COMBUSTION ENGINE WITH EXHAUST GAS TURBOCHARGER
US4261685A (en) * 1978-03-31 1981-04-14 The Garrett Corp. Energy transfer machine
FR2524065A1 (en) * 1982-03-24 1983-09-30 Renault Turbocharger for IC-engine - has sliding gate to control exhaust gas inlet to turbine
EP0095853A1 (en) * 1982-05-28 1983-12-07 Holset Engineering Company Limited A variable inlet area turbine
GB2209802B (en) * 1986-05-13 1990-10-17 Richard John Sauter Centrifugal superchargers
WO1987006981A3 (en) * 1986-05-13 1987-12-30 Richard John Sauter Centrifugal superchargers
GB2209802A (en) * 1986-05-13 1989-05-24 Richard John Sauter Centrifugal superchargers
WO1987006981A2 (en) * 1986-05-13 1987-11-19 Richard John Sauter Centrifugal superchargers
US20040105756A1 (en) * 2002-08-30 2004-06-03 Mitsubishi Heavy Industries, Ltd. Mixed flow turbine and mixed flow turbine rotor blade
US6877955B2 (en) * 2002-08-30 2005-04-12 Mitsubishi Heavy Industries, Ltd. Mixed flow turbine and mixed flow turbine rotor blade
US8845278B2 (en) * 2011-01-27 2014-09-30 Mitsubishi Heavy Industries, Ltd. Radial turbine
US20130136590A1 (en) * 2011-01-27 2013-05-30 Hirotaka Higashimori Radial turbine
US20140328667A1 (en) * 2012-11-09 2014-11-06 Susan J. NENSTIEL Variable geometry diffuser having extended travel and control method thereof
US10378553B2 (en) * 2012-11-09 2019-08-13 Johnson Controls Technology Company Variable geometry diffuser having extended travel and control method thereof
US11092166B2 (en) 2012-11-09 2021-08-17 Johnson Controls Technology Company Variable geometry diffuser having extended travel and control method thereof
US20160208808A1 (en) * 2013-08-26 2016-07-21 Gree Electric Appliances, Inc. Of Zhuhai Regulator assembly and centrifugal compressor
US10082147B2 (en) * 2013-08-26 2018-09-25 Gree Electric Appliances, Inc. Of Zhuhai Regulator assembly and centrifugal compressor
US20150275917A1 (en) * 2014-03-26 2015-10-01 Kabushiki Kaisha Toyota Jidoshokki Centrifugal Compressor
US9874226B2 (en) * 2014-03-26 2018-01-23 Kabushiki Kaisha Toyota Jidoshokki Centrifugal compressor

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