US2823008A - Rotors for fluid flow machines such as turbines - Google Patents

Rotors for fluid flow machines such as turbines Download PDF

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US2823008A
US2823008A US271583A US27158352A US2823008A US 2823008 A US2823008 A US 2823008A US 271583 A US271583 A US 271583A US 27158352 A US27158352 A US 27158352A US 2823008 A US2823008 A US 2823008A
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blades
rotor body
rotor
flow
shroud
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US271583A
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Grey John Constantine
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Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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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
    • 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
    • F01D5/046—Heating, heat insulation or cooling means

Definitions

  • This invention relates to radial-flow turbo-machines, by which is meant radial inward-flow and radial outwardflow turbines, and centrifugal compressors.
  • the invention provides a radial-flow turbo-machine for operation with high-temperature gas, including a bladed rotor of which the parts swept by the hot gas are made of a highly heat-resistant metal, and form a unit or units attached to one or both sides of the rotor body but thermally insulated from said body, which latter is made of a less heat-resistant metal and is relatively massive compared with the said unit.
  • the rotor may be single-sided, comprising a single heat-resistant unit attached to the body on one side of the central plane of said body.
  • the rotor may be double-sided, comprising two heat resistant units, each attached to the body on one side of the central plane of said body.
  • Each said unit may comprise an annular shroud member made of sheet metal and carrying on one face thereof hollow blades of like material, the shroud member being of such dimensions and so attached to the rotor body that shroud and body are separated by a space for a coolant medium.
  • the rotor body may be provided with passageways to permit of maintaining a flow of gaseous coolant through said space.
  • Turbines according to the invention are particularly suitable for incorporation in turbo-superchargers or in continuous-combustion gas turbine plant including a compressor and combustion means, since in either case the compressor provides a ready source of high pressure air which may be used as a coolant for the rotor.
  • Figure 1 is an axial half-section of a single-sided inward-flow turbine.
  • Figure 2 is a perspective view of the annular shroud member with one hollow blade welded in position and another hollow blade detached.
  • Figure 3 is a section on line III--III of Figure 1.
  • Figure 4 is a section in line IVIV of Figure 2.
  • Figure 5 is an axial half-section of a double-sided inward-flow turbine.
  • the radial inward-flow turbine shown in Figures 1 to 4 comprises a casing 1 within which a single-sided impeller is mounted for rotation.
  • the impeller comprises a relatively massive body disc 2 made of ferritic metal or similar material, and hollow metal blades 3 welded to an annular sheet metal shroud 4 which is itself secured to the body 2 by means described below.
  • the hot working fluid enters via the nozzle vanes 5 and flows in a generally radial inward direction through the passages defined by the blades 3 and is discharged in a generally axial direction at 6.
  • the blades 3 and shroud 4 being the main parts of the rotor swept by the hot gases, are made of high temperature-resisting austenitic material.
  • the shroud is of similar contour to the body 2 and is fixed thereto so *nited States Patent 0 ICC that a small clearance space 7 (say about A3 minimum for a small rotor) intervenes between shroud and body.
  • Each blade 3 is U-shaped in transverse section (see Figures 3 and 4) and comprises two similar halves welded together along the line 8, at the base of the U as it were. As shown the resultanthollow blade is closed at the inlet end by pressing the edges together and Welding at 9, while at the outlet end the blades are left open at 10, though the edges are pressed together slightly so that the opening 10 is a mere slit narrower than-the width of the blade cross-section at its largest; Each blade thus completed (and with the outlet edges curved as necessary) is secured to the shroud 4 by welding at eachside'along the line 11.
  • shroud 4 and blades 3 is attached to the body 2 at the periphery by welding to a ring 12 which is bolted to the body 2 and which ring is made of austenitic metal since a part of it is in contact with the hot gases.
  • the shroud 4 is welded at 13a to a ring 13 bolted to the body 2 and is also welded at 14a to a ring or disc '14 bolted to the part 13.
  • the components 13 and 14 may be made of ferritic material as they are not in contact with the hot gases.
  • the shroud 4 is provided with radiating lines of holes 15 which are covered by the blades 3 when aflixed so that these holes provide communication between the space 7 and the hollow interior of each blade. It should be men tioned that the order of assembly may be varied from what has been suggested above e. g. the shroud 4 may be fixed to the body 2 before the blades 3 are attached.
  • the rotor body 2 is centrally bored at 16 and to this boring is supplied a stream of cooling air which, if the turbine forms part of a gas turbine plant, may be derived from the compressor of such plant, since as will appear below the cooling air is required to be at a higher pressure than that of the working fluid flowing between the rotor blades.
  • Passageways 17 radiate from the boring 16 and open into the space 7, while the peripheral ring 12 is provided with an annular series of holes 18 which put the space 7 into communication with the back of the rotor body.
  • the cooling air assisted by centrifugal force flows upwards through the passageways 17 and through the space 7 so that the body 2 is thermally insulated from the shroud 4.
  • cooling air passes through the peripheral holes 18 and of this air some flows round the edge of the ring 12 and mixes with the working fluid while other air may flow radially inward over the rear face of the rotor towards the labyrinth seal 19.
  • Some air enters the interior of the hollow blades 3 by way of the holes 15 and it is expected that in operation conditions will be such that this air will fiow through the slits or outlet openings 10 and join the working fluid at the exhaust.
  • Figure 5 shows a double-sided turbine comprising in efiect two rotors according to Figure I placed back to back, with the necessary structural modification that this involves.
  • the body discs 2 are spigoted for engagement at 29 and bolts 21 are provided to draw the two bodies together and attach them to a shaft.
  • At one side of the rotor axial borings 22 provide communication with the radial passageways 17.
  • the construction is substantially the same as in Figures 1 to 4, and in Figure 5 the same reference numerals are used for parts which correspond or are similar to parts shown in Figures 1 to 4.
  • a bladed rotor for a radial-flow turbo-machine comprising a rotor body, an annular shroud member axially spaced from one side of the said rotor body and hollow blades carried by the shroud member on the side remote from the rotor body, the shroud member having inner and outer peripheral regions at which the shroud member is attached to the said rotor body around the whole circumference of the said peripheral regions only, thereby forming an uninterrupted annular space between the said rotor body and the said shroud member, the rotor body having openings therein communicating with the said space for the flow of coolant therethrough, the shroud member having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted,
  • a bladed rotor for a radial-flow turbo-machine comprising a rotor body, a sheet metal annular shroud member axially spaced from one side of the said rotor body and sheet metal blades of hollow construction carried by the shroud member on the side remote from the motor body, the shroud member having inner and outer peripheral regions at which the shroud member is attached to the said rotor body around the whole circumference of the said peripheral regions only, thereby forming an uninterrupted annular space between the said rotor body and the said shroud member, the rotor body having openings therein communicating with the said space for the flow of coolant therethrough, the shroud member having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted.
  • a bladed rotor for a radial-flow turbo-machine comprising a rotor body, an apertured ring attached to the periphery of the said rotor body, a disc attached to the hub of said rotor body, an annular sheet metal shroud member which is welded to the said ring and disc respectively around the whole of the outer and inner peripheries only of the said shroud member and which, intermediately of the said ring and disc, is separated axially from the rotor body thereby forming an uninterrupted annular space, the rotor body having openings for the flow of coolant to the said space, the coolant leaving through the said apertured ring, and blades carried by the shroud member on the side remote from the rotor body, each of the said blades comprising two strips of sheet metal welded together to form a hollow blade of substantially U-shaped transverse section, the said strips being welded at the open end of the U to the said shroud member, which is provided with apertures communicating with the said hollow blades to
  • a bladed rotor for a radial-flow turbo-machine comprising a rotor body, an annular shroud member axially spaced from one side of the said rotor body and hollow blades carried by the shroud member on the side remote from the rotor body, the shroud member having inner and outer peripheral regions at which the shroud member is attached to the said rotor body, thereby forming an annular space between said rotor body and said shroud member, the rotor body having openings therein communicating with the said space for the flow of coolant therethrough, the shroud member having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted.
  • a bladed rotor for a radial-flow turbo-machine comprising a rotor body, an annular shroud member axially spaced from one side of the said rotor body and hollow blades carried by the shroud member on the side remote from the rotor body, the shroud member having inner and outer peripheral regions at which the shroud member is attached to the said rotor body, thereby forming an annular space between the said rotor body and the said shroud member, the rotor body having an axial throughway therein communicating with radially directed passages communicating with the said space at positions near to the hub of the rotor body for the flow of the coolant thereto and having apertures near to the periphery of the rotor body for the flow of coolant from the said space, the shroud member having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted.
  • a bladed rotor for a radial-flow turbo-machine comprising a rotor body, two annular shroud members which are attached one on each side of the said rotor body at the inner and outer peripheries of the said shroud members and which, intermediately of the said inner and i outer peripheries, are spaced axially from the said rotor body, thereby forming two annular spaces between the said rotor body and the said shroud members and hollow blades carried by the said shroud members on their sides remote from the rotor body, the rotor body having openings therein communicating with the said spaces for the flow of coolant therethrough, the shroud members having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted.

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

Description

J. C. GREY Feb. 11;1958
ROTORS FOR FLUID FLOW MACHINES SUCH AS TURBINES Filed Feb. 14, 195.2
2 Sheets-Sheet 1 Feb. 11; 1958 J. c. GREY ROTORS FOR FLUID FLOW MACHINES SUCH AS TURBINES Filed Feb. 14, 1952 2 'Sheets-Shet 2 l2 l2 9 \K {I 9 f x I I8 l8 3 hf mu 2/ v m, 22 H5. 5,
lnveht-or Lu Attorneys ROTORS FOR FLUID FLOW MACHINES SUCH AS TURBINES John Constantine Grey, Isleworth, England, assignor to Power Jets (Research & Development) Limited, London, England, a British company Application February 14, 1952, Serial No. 271,583
Claims priority, application Great Britain February 15, 1951 6 Claims. (Cl. 25339.15)
This invention relates to radial-flow turbo-machines, by which is meant radial inward-flow and radial outwardflow turbines, and centrifugal compressors.
The invention provides a radial-flow turbo-machine for operation with high-temperature gas, including a bladed rotor of which the parts swept by the hot gas are made of a highly heat-resistant metal, and form a unit or units attached to one or both sides of the rotor body but thermally insulated from said body, which latter is made of a less heat-resistant metal and is relatively massive compared with the said unit.
The rotor may be single-sided, comprising a single heat-resistant unit attached to the body on one side of the central plane of said body.
Alternatively the rotor may be double-sided, comprising two heat resistant units, each attached to the body on one side of the central plane of said body.
Each said unit may comprise an annular shroud member made of sheet metal and carrying on one face thereof hollow blades of like material, the shroud member being of such dimensions and so attached to the rotor body that shroud and body are separated by a space for a coolant medium. In this case the rotor body may be provided with passageways to permit of maintaining a flow of gaseous coolant through said space.
Turbines according to the invention are particularly suitable for incorporation in turbo-superchargers or in continuous-combustion gas turbine plant including a compressor and combustion means, since in either case the compressor provides a ready source of high pressure air which may be used as a coolant for the rotor.
The invention will now be described in more detail in terms of the examples of radial inward flow turbines illustrated in the accompanying drawings, in which:
Figure 1 is an axial half-section of a single-sided inward-flow turbine.
Figure 2 is a perspective view of the annular shroud member with one hollow blade welded in position and another hollow blade detached.
Figure 3 is a section on line III--III of Figure 1.
Figure 4 is a section in line IVIV of Figure 2.
Figure 5 is an axial half-section of a double-sided inward-flow turbine.
The radial inward-flow turbine shown in Figures 1 to 4 comprises a casing 1 within which a single-sided impeller is mounted for rotation. The impeller comprises a relatively massive body disc 2 made of ferritic metal or similar material, and hollow metal blades 3 welded to an annular sheet metal shroud 4 which is itself secured to the body 2 by means described below. The hot working fluid enters via the nozzle vanes 5 and flows in a generally radial inward direction through the passages defined by the blades 3 and is discharged in a generally axial direction at 6. The blades 3 and shroud 4, being the main parts of the rotor swept by the hot gases, are made of high temperature-resisting austenitic material. The shroud is of similar contour to the body 2 and is fixed thereto so *nited States Patent 0 ICC that a small clearance space 7 (say about A3 minimum for a small rotor) intervenes between shroud and body.
Each blade 3 is U-shaped in transverse section (see Figures 3 and 4) and comprises two similar halves welded together along the line 8, at the base of the U as it were. As shown the resultanthollow blade is closed at the inlet end by pressing the edges together and Welding at 9, while at the outlet end the blades are left open at 10, though the edges are pressed together slightly so that the opening 10 is a mere slit narrower than-the width of the blade cross-section at its largest; Each blade thus completed (and with the outlet edges curved as necessary) is secured to the shroud 4 by welding at eachside'along the line 11. The complete 'heat resistant unit -(i. e. shroud 4 and blades 3) is attached to the body 2 at the periphery by welding to a ring 12 which is bolted to the body 2 and which ring is made of austenitic metal since a part of it is in contact with the hot gases. At the hub the shroud 4 is welded at 13a to a ring 13 bolted to the body 2 and is also welded at 14a to a ring or disc '14 bolted to the part 13. The components 13 and 14 may be made of ferritic material as they are not in contact with the hot gases.
From the description it will be seen that the expensive heat resisting austenitic material is confined to sheet metal parts while the relatively massive body 2 is made of ferritic steel and is more convenient to forge because it is not required to carry integral blades.
The shroud 4 is provided with radiating lines of holes 15 which are covered by the blades 3 when aflixed so that these holes provide communication between the space 7 and the hollow interior of each blade. It should be men tioned that the order of assembly may be varied from what has been suggested above e. g. the shroud 4 may be fixed to the body 2 before the blades 3 are attached.
The rotor body 2 is centrally bored at 16 and to this boring is supplied a stream of cooling air which, if the turbine forms part of a gas turbine plant, may be derived from the compressor of such plant, since as will appear below the cooling air is required to be at a higher pressure than that of the working fluid flowing between the rotor blades. Passageways 17 radiate from the boring 16 and open into the space 7, while the peripheral ring 12 is provided with an annular series of holes 18 which put the space 7 into communication with the back of the rotor body. Thus the cooling air assisted by centrifugal force flows upwards through the passageways 17 and through the space 7 so that the body 2 is thermally insulated from the shroud 4. Some of the cooling air passes through the peripheral holes 18 and of this air some flows round the edge of the ring 12 and mixes with the working fluid while other air may flow radially inward over the rear face of the rotor towards the labyrinth seal 19. Some air enters the interior of the hollow blades 3 by way of the holes 15 and it is expected that in operation conditions will be such that this air will fiow through the slits or outlet openings 10 and join the working fluid at the exhaust.
Figure 5 shows a double-sided turbine comprising in efiect two rotors according to Figure I placed back to back, with the necessary structural modification that this involves. For example the body discs 2 are spigoted for engagement at 29 and bolts 21 are provided to draw the two bodies together and attach them to a shaft. At one side of the rotor axial borings 22 provide communication with the radial passageways 17. In other respects the construction is substantially the same as in Figures 1 to 4, and in Figure 5 the same reference numerals are used for parts which correspond or are similar to parts shown in Figures 1 to 4.
Although the invention has been described mainly in terms of turbines it is also applicable to the construction of centrifugal compressors should circumstances arise (for example in chemical process gas turbine plants) where it is desired to compress hot gases.
What I claim is:
1. A bladed rotor for a radial-flow turbo-machine comprising a rotor body, an annular shroud member axially spaced from one side of the said rotor body and hollow blades carried by the shroud member on the side remote from the rotor body, the shroud member having inner and outer peripheral regions at which the shroud member is attached to the said rotor body around the whole circumference of the said peripheral regions only, thereby forming an uninterrupted annular space between the said rotor body and the said shroud member, the rotor body having openings therein communicating with the said space for the flow of coolant therethrough, the shroud member having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted,
2. A bladed rotor for a radial-flow turbo-machine comprising a rotor body, a sheet metal annular shroud member axially spaced from one side of the said rotor body and sheet metal blades of hollow construction carried by the shroud member on the side remote from the motor body, the shroud member having inner and outer peripheral regions at which the shroud member is attached to the said rotor body around the whole circumference of the said peripheral regions only, thereby forming an uninterrupted annular space between the said rotor body and the said shroud member, the rotor body having openings therein communicating with the said space for the flow of coolant therethrough, the shroud member having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted.
3. A bladed rotor for a radial-flow turbo-machine comprising a rotor body, an apertured ring attached to the periphery of the said rotor body, a disc attached to the hub of said rotor body, an annular sheet metal shroud member which is welded to the said ring and disc respectively around the whole of the outer and inner peripheries only of the said shroud member and which, intermediately of the said ring and disc, is separated axially from the rotor body thereby forming an uninterrupted annular space, the rotor body having openings for the flow of coolant to the said space, the coolant leaving through the said apertured ring, and blades carried by the shroud member on the side remote from the rotor body, each of the said blades comprising two strips of sheet metal welded together to form a hollow blade of substantially U-shaped transverse section, the said strips being welded at the open end of the U to the said shroud member, which is provided with apertures communicating with the said hollow blades to allow flow of coolant from the said space into the blades.
4. A bladed rotor for a radial-flow turbo-machine comprising a rotor body, an annular shroud member axially spaced from one side of the said rotor body and hollow blades carried by the shroud member on the side remote from the rotor body, the shroud member having inner and outer peripheral regions at which the shroud member is attached to the said rotor body, thereby forming an annular space between said rotor body and said shroud member, the rotor body having openings therein communicating with the said space for the flow of coolant therethrough, the shroud member having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted.
5. A bladed rotor for a radial-flow turbo-machine comprising a rotor body, an annular shroud member axially spaced from one side of the said rotor body and hollow blades carried by the shroud member on the side remote from the rotor body, the shroud member having inner and outer peripheral regions at which the shroud member is attached to the said rotor body, thereby forming an annular space between the said rotor body and the said shroud member, the rotor body having an axial throughway therein communicating with radially directed passages communicating with the said space at positions near to the hub of the rotor body for the flow of the coolant thereto and having apertures near to the periphery of the rotor body for the flow of coolant from the said space, the shroud member having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted.
6. A bladed rotor for a radial-flow turbo-machine comprising a rotor body, two annular shroud members which are attached one on each side of the said rotor body at the inner and outer peripheries of the said shroud members and which, intermediately of the said inner and i outer peripheries, are spaced axially from the said rotor body, thereby forming two annular spaces between the said rotor body and the said shroud members and hollow blades carried by the said shroud members on their sides remote from the rotor body, the rotor body having openings therein communicating with the said spaces for the flow of coolant therethrough, the shroud members having apertures communicating with the said hollow blades and the blades having outlet openings, flow of coolant through the blades thereby being permitted.
References Cited in the file of this patent UNITED STATES PATENTS Germany Sept.
US271583A 1951-02-15 1952-02-14 Rotors for fluid flow machines such as turbines Expired - Lifetime US2823008A (en)

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GB3690/51A GB705387A (en) 1951-02-15 1951-02-15 Improvements relating to radial-flow turbine or centrifugal compressors

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Cited By (12)

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US2919103A (en) * 1952-12-24 1959-12-29 Garrett Corp Means for cooling the peripheral rim of a centripetal turbine wheel
US3133693A (en) * 1962-05-17 1964-05-19 Gen Electric Sump seal system
US3167301A (en) * 1962-03-16 1965-01-26 Garrett Corp Turbine wheel exducer structure
US3582232A (en) * 1969-06-02 1971-06-01 United Aircraft Canada Radial turbine rotor
US3945101A (en) * 1973-02-22 1976-03-23 Motoren-Und Turbinen Union Munich Gmbh Rotor wheel for radial-flow fans and turbines and method and fixture for making same
US4150919A (en) * 1977-06-10 1979-04-24 Wallace Murray Corporation Radiator cooling fan construction
US4253031A (en) * 1978-05-27 1981-02-24 Robert Bosch Gmbh Directly driven dynamo electric machine-gas turbine generator structure
US20070065276A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Impeller for a centrifugal compressor
US20070063449A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Stationary seal ring for a centrifugal compressor
US20070065277A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Centrifugal compressor including a seal system
EP2072830A2 (en) * 2007-12-21 2009-06-24 Pratt & Whitney Canada Corp. Centrifugal impeller with internal heating
US10316667B2 (en) * 2015-07-29 2019-06-11 Korea Maritime University Industry-Academic Cooperation Foundation Apparats for decreasing thrust of radial inflow turbine

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DE1296875B (en) * 1962-02-09 1969-06-04 Laval Turbine Runner for a centripetal gas turbine
FR2552817B1 (en) * 1978-11-27 1988-02-12 Snecma IMPROVEMENTS IN COOLING TURBINE ROTORS
GB2239491B (en) * 1989-11-28 1993-09-29 Copermill Ltd Hot gas blower
DE4417095A1 (en) * 1994-05-16 1995-11-23 Abb Management Ag Impeller of radial compressor
GB2354043A (en) * 1999-08-24 2001-03-14 Fred Starr Cooling radial flow turbine
DE10357711A1 (en) * 2003-12-09 2005-07-14 Abb Turbo Systems Ag cooling method
US7559745B2 (en) * 2006-03-21 2009-07-14 United Technologies Corporation Tip clearance centrifugal compressor impeller
DE102006048784A1 (en) * 2006-10-12 2008-04-17 Man Diesel Se Compressor for a turbocharger and method for its cooling
US9650916B2 (en) 2014-04-09 2017-05-16 Honeywell International Inc. Turbomachine cooling systems

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US2058479A (en) * 1933-03-10 1936-10-27 Milo Ab Turbine for hot driving media
US2190245A (en) * 1938-03-02 1940-02-13 Page M Sartell Pump for compressible fluids
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US2390506A (en) * 1942-05-23 1945-12-11 Buchi Alfred Turbine with overhung rotor
US2447292A (en) * 1943-10-12 1948-08-17 Joseph E Van Acker Gas-actuated turbine-driven compressor
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US2465671A (en) * 1944-05-10 1949-03-29 Power Jets Res & Dev Ltd Centrifugal compressor, pump, and the like
US2464754A (en) * 1944-08-21 1949-03-15 American Steel Foundries Brake rotor
US2598176A (en) * 1947-03-11 1952-05-27 Power Jets Res & Dev Ltd Sealing device
US2606741A (en) * 1947-06-11 1952-08-12 Gen Electric Gas turbine nozzle and bucket shroud structure
US2643851A (en) * 1948-05-27 1953-06-30 Gen Electric Turbo-machine rotor with cooling means
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2919103A (en) * 1952-12-24 1959-12-29 Garrett Corp Means for cooling the peripheral rim of a centripetal turbine wheel
US3167301A (en) * 1962-03-16 1965-01-26 Garrett Corp Turbine wheel exducer structure
US3133693A (en) * 1962-05-17 1964-05-19 Gen Electric Sump seal system
US3582232A (en) * 1969-06-02 1971-06-01 United Aircraft Canada Radial turbine rotor
US3945101A (en) * 1973-02-22 1976-03-23 Motoren-Und Turbinen Union Munich Gmbh Rotor wheel for radial-flow fans and turbines and method and fixture for making same
US4150919A (en) * 1977-06-10 1979-04-24 Wallace Murray Corporation Radiator cooling fan construction
US4253031A (en) * 1978-05-27 1981-02-24 Robert Bosch Gmbh Directly driven dynamo electric machine-gas turbine generator structure
US20070065276A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Impeller for a centrifugal compressor
US20070063449A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Stationary seal ring for a centrifugal compressor
US20070065277A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Centrifugal compressor including a seal system
EP2072830A2 (en) * 2007-12-21 2009-06-24 Pratt & Whitney Canada Corp. Centrifugal impeller with internal heating
EP2072830A3 (en) * 2007-12-21 2012-05-09 Pratt & Whitney Canada Corp. Centrifugal impeller with internal heating
US10316667B2 (en) * 2015-07-29 2019-06-11 Korea Maritime University Industry-Academic Cooperation Foundation Apparats for decreasing thrust of radial inflow turbine

Also Published As

Publication number Publication date
GB705387A (en) 1954-03-10
DE1046408B (en) 1958-12-11

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