US2609141A - Centrifugal compressor - Google Patents

Centrifugal compressor Download PDF

Info

Publication number
US2609141A
US2609141A US619774A US61977445A US2609141A US 2609141 A US2609141 A US 2609141A US 619774 A US619774 A US 619774A US 61977445 A US61977445 A US 61977445A US 2609141 A US2609141 A US 2609141A
Authority
US
United States
Prior art keywords
rotor
axis
axes
centrifugal compressor
cross
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US619774A
Inventor
Aue George
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sulzer AG
Original Assignee
Sulzer AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Sulzer AG filed Critical Sulzer AG
Application granted granted Critical
Publication of US2609141A publication Critical patent/US2609141A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/16—Centrifugal pumps for displacing without appreciable compression
    • F04D17/165—Axial entry and discharge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • Thediffusors are preferably of, circular" cross- -section.
  • the channel'smf the intermediate-mem- 'ber which guide and turn-the'floir'rromrrotor "to diifusors, may at the rotor end be of approximately rectangular cross-section and at the diffusor end of circular cross section, both with about the samecross-sectional-area. It is admantageousior these :directing channels, :and the difiusors connected to them; to be'contai-ned between an-outer guidecasing and'an inner guide member in the form of a'body of revolution symmetrical with respect to the'rotor axis.
  • FIG. 1 shows an axial cross-section,ofla cen- Itrifugal compressor
  • 'Figs..2,3. and 4 show sections onthe planes I-,-I II-"-II. and III-+III of Fig. 1;
  • Fig. 5. shows an end view of. the compressorin part section on the planes 1-11 and.II-..II. of Fi 1;
  • the rotor 2 At theinlet efidhth'egshafi I axis a: in order to prevent bending stresses being caused by centrifugal forces.
  • the rotor 2 can be driven at a correspondingly high velocity, which may in certain circumstances be greater than the velocity of sound in the medium handled, for instance at 330 metres per sec. and more, without the absolute outlet velocity of the medium delivered by the rotor 2 exceeding or reaching this velocity of sound, the tapering screw-line of the blades 8 being arranged in the direction of rotation opposite to that of the rotor and thus ensuring an outlet angle on the rotor 2 in accordance with this requirement.
  • the intermediate piece lying between the cross-sectional planes I1 and IIII is provided with directing channels I2, which are formed by the casing 9, the guide member 6 and the partition walls II. It would be possible in the intermediate piece to form the partition walls of the channels as blade grids,
  • the channels l2 are bent from a direction parallel to the rotor blades to a direction parallel to the difiusor axes Y in such a way that the medium flowing out from the rotor in a direction oblique to the rotor axis, is deviated into a direction at least approximately parallel to the rotor axis.
  • the channels I2 are of rectangular crosssection as shown in Fig. 2, the partition walls being then thin and offering only slight resistance to the medium flowing in.
  • the cross-section of the channels l2 changes its shape continually along the axis of flow through the intermediate piece in order to form on reaching the transverse plane IIII, shown in Figs. 3 and 5, a circular cross-section of about the same area as the rectangular entry cross-section (I-I).
  • the channels l2 lead into diffusers l3, which are for the most part straight and contained between casing 9 and guide member 6, the circular cross-sections gradually widening, so that the conversion from velocity energy into pressure energy takes place under the most favourable conditions.
  • the axes y of the diifusors [3 may then cut the axis :r of the rotor at infinity or at a finite point or may be arranged oblique to but not intersecting it, as shown in Figs. 6-8. From the diffusors l3 the medium handled arrives approximately free from twist and with components of velocity mostly parallel to the axis into the angular space 14 between the guide casing 9 and the guide member 6 and leaves it through the pipe l5 leading to the point of use.
  • channels l2 and the diffusors l3 being formed as hollow spaces in a cast piece as .4 in the embodiment illustrated in Figs. 1-5, they could, without departing from the invention, also be made of sheet metal and so supported with respect to each other that the desired mutual position is ensured. In this way it would be possible to reduce the weight of the compressor considerably. i
  • a centrifugal compressor assembly for producing a high stage pressure ratio, including in combination an approximately conical rotor arranged to discharge at its bigger end, a, plurality of stationary diffusors arranged around the rotor axis with their inlet ends toward the rotor discharge end but axially displaced therefrom, said diffusors having circular cross-sections and generally straight axes the directions of these axes deviating by less than 20 from the direction of the rotor axis, and a stationary intermediate portion between the rotor discharge end and the difiusor inlet ends provided with directing channels, matching, as to cross-section and direction, at the one end with the diffusor inlet ends and. having curved axes and along these curved axes cross-sections of substantially constant area but continually variable shape, to match, as to crosssection and direction, at the other end with the discharge from said rotor.

Landscapes

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

Description

Sept. 2, 1952 m; 2,609 141 CENTRIFUGAL COMPRESSOR Filed Oct. 2, 1945 2 SHEETS-SHEET 1 Sept. 2, 1952 G. AUE 2,609,141
CENTRIFUGAL COMPRESSOR Filed Oct. 2, 1945 2 SHEETS-SHEET 2 INVENTOR Geafy flue BY Q WAQXMR L Qwm ATTORNEYS Patented Sept. 2, i952 PATENT JOFIFICE goenran uoer COMPRESSOR Georg Aue, Winte1{thur, Switzerland, assignor to Sulzer Frer'es. Societe Anonyme, Winterthur,
Switzerland Application.OctobciiZ. 1945.;SierialNo. 619,774.- ."Inifiwit'zerland October 2.19M
'{=locity" into-- a directionat least-approximately parallel 'to' the -rotcir axis and "leading to diffusers having generally'straight axes '-in-=-which' that medi'um is then slowed down. I
In employing the wcrd "axesto describe the central or median lines about which thediifu'sors are arranged applicantdoes -net intend to limit 'such lines to the: rigid geometric straigh-tnessof an axis of rota-tion, but rather to include lines having sligh-t and aerodynamically.unimportant depar-tures from such straightness. l See, New entury Dictionaryy2-vol; ed, September 1930.
Thediffusors are preferably of, circular" cross- -section. The channel'smf the intermediate-mem- 'ber which guide and turn-the'floir'rromrrotor "to diifusors, may at the rotor end be of approximately rectangular cross-section and at the diffusor end of circular cross section, both with about the samecross-sectional-area. It is admantageousior these :directing channels, :and the difiusors connected to them; to be'contai-ned between an-outer guidecasing and'an inner guide member in the form of a'body of revolution symmetrical with respect to the'rotor axis. The; axes of the difiusors themselves-may cut the; rotor axis atanyfinite'point or -at infinity, ior theytmay be arranged oblique to but -not-intersecting it.
ln fthe conversion ct -energy "in a centrifugal blower theefficiencyof the diffuser plays; an ,important part; since; as "is known; only about .one- "half to three-quarters of "the delivery pressureis produced up to-the-outl-et of the rotor, whilst the r exis in the-issuing delivered medium in the form of .kinetic energy and has to be converted ,astar a's possible into pressurelin the diffusor.
fillll'hepest efficiency of lallifdesigns ofedifiusors ispossessedby'thosewhich consist of a comically expanding pipe of circular cross-section having a. straight axis. In radial compressors it is old to divide the air-stream issuing from the rotor into separate streams by means of a suitably subdivided guide spiral and to turn these streams from that spiral into straight-axis difl'usorsg ly ing in planes at right angles to the rotor axis. These streams are slowed down inthe diflusors and thus obtain pressure, the retarded stream issuing, if required, into ;a bladelcss-spiral casing,
Whereafter further turning iiiplanes 'at -ri'gh't angles "to the rotor axis, it is led to the outlet branches. Such-spirals with straight-axis diffusors-have large diameters and therefore take up, much space radially, so that,-apart-fromthe drawback ofincreasing-the weight" and the great cost of manufacturing such --a 1 spiral, it is ;jdifficultto fit such a-compressor intoa piantzasan auxiliary machine. In addition;suchknown outletspirals equipped with diffusers can' only -be adopted for centrifugal machines With-radialilow of the medium handled. An obvious means-of reducingjthe diameter ofthe spiralcasin is to construct thediffusor with the axis bent. iiBut then additional Coriolis and -,centrifugal*fo1 ces make their appearance in the medium handled, causing the flow of the medium ;to be deflected {from the guiding Walls and thus giving always aworse diffusorefficiency than-with straight-linediifusors. :Also diffusorswith cross- 'jectedto' the braking action of the walls ontwo sides. The alternative drawbacks of comparatively' large casing diameters ordiffusoli with a poor. degreev of efficiency can both be; avoided by the present invention.
Embodiments of theinvention are illustrated by. Way-0f example in theaccompanying drawing, in which:
"Fig. 1 shows an axial cross-section,ofla cen- Itrifugal compressor; 'Figs..2,3. and 4 show sections onthe planes I-,-I II-"-II. and III-+III of Fig. 1;
Fig. 5.shows an end view of. the compressorin part section on the planes 1-11 and.II-..II. of Fi 1; and
'fFi sinclusive,.reprersentldifierentforms oiarransement oi thedifiusors. g The sh ft l of the. rotor ;.2;is... .arried @in.-.;the bea'rings"3 ana t. The-bearings 'is-arrangediin thewinlfit c n p aniline. bearing .4. in .the
,guidemember 5. At theinlet efidhth'egshafi I axis a: in order to prevent bending stresses being caused by centrifugal forces. In order to obtain a high-stage-pressure ratio the rotor 2 can be driven at a correspondingly high velocity, which may in certain circumstances be greater than the velocity of sound in the medium handled, for instance at 330 metres per sec. and more, without the absolute outlet velocity of the medium delivered by the rotor 2 exceeding or reaching this velocity of sound, the tapering screw-line of the blades 8 being arranged in the direction of rotation opposite to that of the rotor and thus ensuring an outlet angle on the rotor 2 in accordance with this requirement.
The guide member 6, formed as a solid of revolution symmetrical with respect to the rotor axis x, is arranged at the outlet end of the rotor 2. Both the rotor 2 and the guide member 6 are surrounded by the casing 9, which is connected at the inlet end to the inlet casing part by supporting ribs l0, and to the guide member 6 by the partition walls II. The intermediate piece lying between the cross-sectional planes I1 and IIII is provided with directing channels I2, which are formed by the casing 9, the guide member 6 and the partition walls II. It would be possible in the intermediate piece to form the partition walls of the channels as blade grids,
which particularly for rotors with slow specific speed, whose stream issuing from the rotor requires to be greatly deviated, could be formed as split wings. The channels l2 are bent from a direction parallel to the rotor blades to a direction parallel to the difiusor axes Y in such a way that the medium flowing out from the rotor in a direction oblique to the rotor axis, is deviated into a direction at least approximately parallel to the rotor axis. At the inlet side of the intermediate piece, the channels I2 are of rectangular crosssection as shown in Fig. 2, the partition walls being then thin and offering only slight resistance to the medium flowing in. The cross-section of the channels l2 changes its shape continually along the axis of flow through the intermediate piece in order to form on reaching the transverse plane IIII, shown in Figs. 3 and 5, a circular cross-section of about the same area as the rectangular entry cross-section (I-I).
By doing without a difiusor effect in this intermediate piece, the flow is prevented as much as possible from leaving the guiding Walls. Approximately from the section IIII downwards, the channels l2 lead into diffusers l3, which are for the most part straight and contained between casing 9 and guide member 6, the circular cross-sections gradually widening, so that the conversion from velocity energy into pressure energy takes place under the most favourable conditions. The axes y of the diifusors [3 may then cut the axis :r of the rotor at infinity or at a finite point or may be arranged oblique to but not intersecting it, as shown in Figs. 6-8. From the diffusors l3 the medium handled arrives approximately free from twist and with components of velocity mostly parallel to the axis into the angular space 14 between the guide casing 9 and the guide member 6 and leaves it through the pipe l5 leading to the point of use.
Instead of the channels l2 and the diffusors l3 being formed as hollow spaces in a cast piece as .4 in the embodiment illustrated in Figs. 1-5, they could, without departing from the invention, also be made of sheet metal and so supported with respect to each other that the desired mutual position is ensured. In this way it would be possible to reduce the weight of the compressor considerably. i
It would also be possible for the axes of all diifusors to be parallel to each other, but nevertheless slightly inclined to the rotor axis. Likewise the point of intersection of the diflusor axes might lie outside the rotor axis.
I claim:
1. A centrifugal compressor assembly for producing a high stage pressure ratio, including in combination an approximately conical rotor arranged to discharge at its bigger end, a, plurality of stationary diffusors arranged around the rotor axis with their inlet ends toward the rotor discharge end but axially displaced therefrom, said diffusors having circular cross-sections and generally straight axes the directions of these axes deviating by less than 20 from the direction of the rotor axis, and a stationary intermediate portion between the rotor discharge end and the difiusor inlet ends provided with directing channels, matching, as to cross-section and direction, at the one end with the diffusor inlet ends and. having curved axes and along these curved axes cross-sections of substantially constant area but continually variable shape, to match, as to crosssection and direction, at the other end with the discharge from said rotor.
2. A centrifugal compressor assembly as claimed in claim 1, the directing channels and the diffusors of which are contained between a. guide casing and a guide member, said member forming a solid of revolution symmetrical to the rotor axis.
3. A centrifugal compressor assembly as claimed in claim 1, the axes of whose difiusors intersect the rotor axis at a finite point.
4. A centrifugal compressor assembly as claimed in claim 1, the axes of whose difiusors intersect the rotor axis at infinity.
5. A centrifugal compressor assembly as claimed in claim 1, the axes of whose diffusors being arranged oblique to the rotor axis but not intersecting it.
GEORG AUE.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 521,962 McConnell et a1. June 26, 1894 1,042,506 De Vallat Oct. 29, 1912 1,430,141 Angus Sept. 26, 1922 1,771,939 Rees July 29, 1930 1,785,354 Lawaczeck Dec. 16, 1930 1,932,231 Schmidt Oct. 24, 1933 1,959,703 Bermann May 22, 1934 2,463,976 Kilchenmann Mar. 8, 1949 FOREIGN PATENTS Number Country Date 274,224 Italy 1930 409,450 Germany Feb. 6, 1925
US619774A 1944-10-02 1945-10-02 Centrifugal compressor Expired - Lifetime US2609141A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH243902T 1944-10-02

Publications (1)

Publication Number Publication Date
US2609141A true US2609141A (en) 1952-09-02

Family

ID=4463893

Family Applications (1)

Application Number Title Priority Date Filing Date
US619774A Expired - Lifetime US2609141A (en) 1944-10-02 1945-10-02 Centrifugal compressor

Country Status (6)

Country Link
US (1) US2609141A (en)
CH (1) CH243902A (en)
DE (1) DE885454C (en)
FR (1) FR914420A (en)
GB (1) GB604378A (en)
NL (1) NL67267C (en)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658338A (en) * 1946-09-06 1953-11-10 Leduc Rene Gas turbine housing
US2889107A (en) * 1955-01-03 1959-06-02 Stalker Corp Fluid rotor construction
US2952403A (en) * 1954-04-22 1960-09-13 Edward A Stalker Elastic fluid machine for increasing the pressure of a fluid
US2955746A (en) * 1954-05-24 1960-10-11 Edward A Stalker Bladed fluid machine for increasing the pressure of a fluid
US2991927A (en) * 1958-02-03 1961-07-11 Thomas E Quick Apparatus for moving fluids
US3028140A (en) * 1957-06-17 1962-04-03 James R Lage Rotary fluid flow machine having rotor vanes constructed according to three dimensional calculations
US3059833A (en) * 1956-10-17 1962-10-23 Remi A Benoit Fans
US3150823A (en) * 1962-02-12 1964-09-29 Ass Elect Ind Diffusers
US3837762A (en) * 1972-05-31 1974-09-24 English Electric Co Ltd Pumps
US3860360A (en) * 1973-09-04 1975-01-14 Gen Motors Corp Diffuser for a centrifugal compressor
US4211514A (en) * 1976-12-22 1980-07-08 Airscrew Howden Limited Mixed flow fan
US4462751A (en) * 1982-03-24 1984-07-31 Borg-Warner Corporation Centrifugal pump improvement
EP0201318A2 (en) * 1985-05-08 1986-11-12 AlliedSignal Inc. High efficiency transonic mixed-flow compressor method and apparatus
US6471475B1 (en) * 2000-07-14 2002-10-29 Pratt & Whitney Canada Corp. Integrated duct diffuser
US20050214109A1 (en) * 2004-02-23 2005-09-29 Grande Salvatore F Iii Bladeless conical radial turbine and method
US20120138058A1 (en) * 2009-08-11 2012-06-07 Timothy Tsun-Fai Fu Single stage, axial symmetric blower and portable ventilator
US20150167675A1 (en) * 2013-12-18 2015-06-18 Man Diesel & Turbo Se Radial compressor and compressor arrangement with such a radial compressor
US20160076554A1 (en) * 2014-09-11 2016-03-17 Hamilton Sundstrand Corporation Backing plate
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11187243B2 (en) 2015-10-08 2021-11-30 Rolls-Royce Deutschland Ltd & Co Kg Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine
US11998690B2 (en) 2020-11-03 2024-06-04 Resmed Motor Technologies Inc. Single stage, axial symmetric blower and portable ventilator

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE968101C (en) * 1950-03-03 1958-01-16 Escher Wyss Gmbh Equipment on radial centrifugal compressors and pumps for converting kinetic energy of the flow medium into pressure energy
US2708883A (en) * 1950-03-03 1955-05-24 Escher Wyss Ag Arrangement for use in radial centrifugal compressors and pumps for the conversion of kinetic energy of the flowing medium into pressure energy
US2743053A (en) * 1950-10-27 1956-04-24 Fairchild Engine & Airplane Fluid impeller structure
DE1024673B (en) * 1953-08-12 1958-02-20 Alois Mueller & Sohn G M B H M Radial fan with axial entry and deflection of the flow emerging from the impeller into an axial ring channel
US4100732A (en) * 1976-12-02 1978-07-18 General Electric Company Centrifugal compressor advanced dump diffuser
FR2772843B1 (en) * 1997-12-19 2000-03-17 Snecma DEVICE FOR TRANSFERRING FLUID BETWEEN TWO SUCCESSIVE STAGES OF A MULTI-STAGE CENTRIFUGAL TURBOMACHINE
US6280139B1 (en) 1999-10-18 2001-08-28 Pratt & Whitney Canada Corp. Radial split diffuser

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US521862A (en) * 1894-06-26 Ventilating-fan
US1042506A (en) * 1912-03-15 1912-10-29 Charles Emile Jules De Vallat Propeller.
US1430141A (en) * 1920-04-07 1922-09-26 Atlas Engineering & Machine Co Accelerating pump for water-heating systems
DE409450C (en) * 1925-02-06 Harald Jensen Hydraulic drive arrangement
US1771939A (en) * 1926-10-19 1930-07-29 Rees Edmund Scott Gustave Propeller, pump, or fan
US1785354A (en) * 1926-01-19 1930-12-16 Worthington Pump & Mach Corp Hydraulic machine
US1932231A (en) * 1930-02-28 1933-10-24 Westinghouse Electric & Mfg Co Propeller type fluid translating device
US1959703A (en) * 1932-01-26 1934-05-22 Birmann Rudolph Blading for centrifugal impellers or turbines
US2463976A (en) * 1942-02-21 1949-03-08 Sulzer Ag High-pressure compressor

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US521862A (en) * 1894-06-26 Ventilating-fan
DE409450C (en) * 1925-02-06 Harald Jensen Hydraulic drive arrangement
US1042506A (en) * 1912-03-15 1912-10-29 Charles Emile Jules De Vallat Propeller.
US1430141A (en) * 1920-04-07 1922-09-26 Atlas Engineering & Machine Co Accelerating pump for water-heating systems
US1785354A (en) * 1926-01-19 1930-12-16 Worthington Pump & Mach Corp Hydraulic machine
US1771939A (en) * 1926-10-19 1930-07-29 Rees Edmund Scott Gustave Propeller, pump, or fan
US1932231A (en) * 1930-02-28 1933-10-24 Westinghouse Electric & Mfg Co Propeller type fluid translating device
US1959703A (en) * 1932-01-26 1934-05-22 Birmann Rudolph Blading for centrifugal impellers or turbines
US2463976A (en) * 1942-02-21 1949-03-08 Sulzer Ag High-pressure compressor

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658338A (en) * 1946-09-06 1953-11-10 Leduc Rene Gas turbine housing
US2952403A (en) * 1954-04-22 1960-09-13 Edward A Stalker Elastic fluid machine for increasing the pressure of a fluid
US2955746A (en) * 1954-05-24 1960-10-11 Edward A Stalker Bladed fluid machine for increasing the pressure of a fluid
US2889107A (en) * 1955-01-03 1959-06-02 Stalker Corp Fluid rotor construction
US3059833A (en) * 1956-10-17 1962-10-23 Remi A Benoit Fans
US3028140A (en) * 1957-06-17 1962-04-03 James R Lage Rotary fluid flow machine having rotor vanes constructed according to three dimensional calculations
US2991927A (en) * 1958-02-03 1961-07-11 Thomas E Quick Apparatus for moving fluids
US3150823A (en) * 1962-02-12 1964-09-29 Ass Elect Ind Diffusers
US3837762A (en) * 1972-05-31 1974-09-24 English Electric Co Ltd Pumps
US3860360A (en) * 1973-09-04 1975-01-14 Gen Motors Corp Diffuser for a centrifugal compressor
US4211514A (en) * 1976-12-22 1980-07-08 Airscrew Howden Limited Mixed flow fan
US4462751A (en) * 1982-03-24 1984-07-31 Borg-Warner Corporation Centrifugal pump improvement
EP0201318A2 (en) * 1985-05-08 1986-11-12 AlliedSignal Inc. High efficiency transonic mixed-flow compressor method and apparatus
US4678398A (en) * 1985-05-08 1987-07-07 The Garrett Corporation High efficiency transonic mixed-flow compressor method and apparatus
EP0201318A3 (en) * 1985-05-08 1988-06-29 The Garrett Corporation High efficiency transonic mixed-flow compressor method and apparatus
US6471475B1 (en) * 2000-07-14 2002-10-29 Pratt & Whitney Canada Corp. Integrated duct diffuser
US20050214109A1 (en) * 2004-02-23 2005-09-29 Grande Salvatore F Iii Bladeless conical radial turbine and method
US7192244B2 (en) 2004-02-23 2007-03-20 Grande Iii Salvatore F Bladeless conical radial turbine and method
US20120138058A1 (en) * 2009-08-11 2012-06-07 Timothy Tsun-Fai Fu Single stage, axial symmetric blower and portable ventilator
US10874810B2 (en) 2009-08-11 2020-12-29 Resmed Motor Technologies Inc. Single stage, axial symmetric blower and portable ventilator
US9861774B2 (en) * 2009-08-11 2018-01-09 Resmed Motor Technologies Inc. Single stage, axial symmetric blower and portable ventilator
US20150167675A1 (en) * 2013-12-18 2015-06-18 Man Diesel & Turbo Se Radial compressor and compressor arrangement with such a radial compressor
US9790945B2 (en) * 2013-12-18 2017-10-17 Man Diesel & Turbo Se Radial compressor and compressor arrangement with such a radial compressor
US9863439B2 (en) * 2014-09-11 2018-01-09 Hamilton Sundstrand Corporation Backing plate
US20160076554A1 (en) * 2014-09-11 2016-03-17 Hamilton Sundstrand Corporation Backing plate
US11187243B2 (en) 2015-10-08 2021-11-30 Rolls-Royce Deutschland Ltd & Co Kg Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11815047B2 (en) 2020-07-14 2023-11-14 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine
US11998690B2 (en) 2020-11-03 2024-06-04 Resmed Motor Technologies Inc. Single stage, axial symmetric blower and portable ventilator

Also Published As

Publication number Publication date
CH243902A (en) 1946-08-15
FR914420A (en) 1946-10-08
NL67267C (en) 1950-12-29
DE885454C (en) 1953-11-12
GB604378A (en) 1948-07-02

Similar Documents

Publication Publication Date Title
US2609141A (en) Centrifugal compressor
US3333762A (en) Diffuser for centrifugal compressor
US3552877A (en) Outlet housing for an axial-flow turbomachine
US3420435A (en) Diffuser construction
US3356289A (en) Supersonic compressors of the centrifugal or axial flow and centrifugal types
US2918254A (en) Turborunner
US3824029A (en) Centrifugal supersonic compressor
US4325672A (en) Regenerative turbo machine
US4012166A (en) Supersonic shock wave compressor diffuser with circular arc channels
US2689681A (en) Reversely rotating screw type multiple impeller compressor
US1075300A (en) Centrifugal compressor.
JPS6390630A (en) Axial-flow turbine
JP2007100701A (en) Steam turbine exhaust diffuser
US3108955A (en) Hollow rotors and centrifuges
US2795373A (en) Guide vane assemblies in annular fluid ducts
US3724968A (en) Axial supersonic compressor
US2925954A (en) Compressor group with intercooler
US3128939A (en) Szydlowski
US4390319A (en) Turbine exhaust hood
US2965287A (en) Radial flow compressor
US2311024A (en) Guide apparatus for centrifugal blowers and pumps
US2438426A (en) Centrifugal compressor
CN110418896A (en) It returns and draws grade and radial turbine fluid energy machine
JP5693112B2 (en) Axial turbine and method for exhausting flow from an axial turbine
US2635849A (en) Turbine stage