US3112866A - Compressor blade structure - Google Patents

Compressor blade structure Download PDF

Info

Publication number
US3112866A
US3112866A US121875A US12187561A US3112866A US 3112866 A US3112866 A US 3112866A US 121875 A US121875 A US 121875A US 12187561 A US12187561 A US 12187561A US 3112866 A US3112866 A US 3112866A
Authority
US
United States
Prior art keywords
blade
blades
row
rotor
section
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
US121875A
Other languages
English (en)
Inventor
Fortescue Peter
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.)
General Dynamics Corp
Original Assignee
General Dynamics Corp
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 General Dynamics Corp filed Critical General Dynamics Corp
Priority to US121875A priority Critical patent/US3112866A/en
Priority to GB25533/62A priority patent/GB951713A/en
Priority to CH807062A priority patent/CH428071A/de
Priority to DE19621428098 priority patent/DE1428098A1/de
Application granted granted Critical
Publication of US3112866A publication Critical patent/US3112866A/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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • 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
    • 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
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

Definitions

  • an ⁇ arial iiow compressor having rotor and Vstator blade profiles which are substantially symmetrical and suitably proportioned with individual sections to effect diffusion and deflection of the gas flow, various of lthe limitations which reduce the amount of effective compression wori; that can be accomplished by each stage ycan be obviated. More particularly, if each of the symmetrical rotor and stator blade rows is provided with a section for diffusing the gas flow passing therethrough with a corresponding static pressure increase and a second sect-ion for effecting ⁇ a substantial deflection of the gas flow without a corresponding pressure increase substantially more work per compressor stage can be achieved than can be obtained from a conventional compression stage operating at the same or even a somewhat higher blade speed.
  • a further object of the invention resides in the provision of an improved compressor blade structure which yields a high degree of compression while utilizing a relatively few number of stages.
  • Still another object of the invention is to provide a symmetrical blading configuration which can be adapted for use in an axial flow compressor unit; the rotor and stator stages or" which are each provided with a blade configuration to effect the diiusion of the ⁇ gas flow passing therethrough and a blade configuration to provide the separate function of deflecting the gas through a desired angle without a pressure increase so that a maximum amount of compression work at a selected blade velocity can be achieved.
  • a more finite object of the invention is to provide a blading configuration which is capable of compressing a fluid medium while operating at relatively low rotational velocity and which can be suitably adapted for utilization in any number of axial flow compressors and similar fluid working applications.
  • FIGURE l is a fragmentary sectional view of a preferred embodiment of the compressor blade structure as adapted for utilization in a conventional axial flow compressor unit;
  • FIGURE 2 is a fragmentary diagrammatic plan View of the rotor and stator components of one stage of a compressor as contemplated by the present invention
  • FIGURE 3 is a-fragmentary sectional view taken along the line 3 3 in FIGURE l;
  • FIGURE 4 is a fragmentary diagrammatic plan view corresponding to FIGURE 2 but illustrating another embodiment of the invention.
  • FIGURE 5 is still another fragmentary diagrammatic plan view of a third embodiment of the compressor blade structure contemplated by the present invention.
  • an axial flow compressor unit is adapted with a conventional rc action rotor blade row that is followed by an impulse or iiow reversing rotor blade row having an equal or greater number of blades.
  • the reaction and impulse rotor blade rows which are mounted for concomitant rotation in lixed relation on a driven shaft of the compressor unit, are followed by a pair of stator blade rows that are identical to the rotor blade rows although reversed by 180 (ie. a mirror image thereof).
  • reaction blades of both the rotor and stator blade rows function to effect the diffusion of the gas flow during the passage of the gas therethrough, and the impulse blades accomplish a substantial deection of the diffused gas ilow without a corresponding static pressure increase.
  • This combination of reaction and impulse blade rows results in the production of a maximum amount of compression work per stage for a given blade velocity.
  • FEGURE 5 illustrates still another embodiment of the compressor blade structure contemplated by the present invention. As depicted in the drawing, this embodiment utilizes a rotor of pure impulse or ow reversing blades. On additional section of blades is utilized, which is an extension of the stator reaction blade section. In this alternate embodiment, a pressure rise through the principle of diffusion is effected in the reaction section of the stator blade row while the function of the impulse rotor stage and impulse section of the stator stage is to accomplish delection of the gas low during the passage thereof through these blade sections.
  • a compressor adapted with one preferred embodiment of the blade structure contemplated by the present invention, includes a housing lil having an inner wall that encompasses one or more compressor stages, each of which includes a dual rotor blade row 11 and a. dual stator blade row 12.
  • Each dual rotor blade row il includes a row containing a plurality of reaction blades lia and a row having a corresponding number of impulse or low reversing rotor blades 11b.
  • the blades lla and 11b extend radially outwardly from a hub i3 which is secured for rotary movement to a driven shaft 1 4.
  • each of lthe rotor blades 11a and 1lb is structurally secured to a base plate or platform 16.
  • Each of the base plates i6 is formed within a dove tail section 16a that is iixedly secured within a suitably proportioned slot i7 formed on the periphery of the hub 13.
  • the cylindrical hub 13 is provided with a plurality of spaced-apart slots i7 about the periphery thereof wherein the rotor blades 11a and 1lb are secured for rotation therewith.
  • the stator blades 12a and 12b extend radially inwardly from the wall of the housing l() between alternate dual rotor blade rows.
  • portions of the inner wall of the housing 1G have suitably proportioned slots it provided therein.
  • Each of the slots i9 are adapted to accommodate a dove tail section 2i. extending from a base plate or blade platform 22 whereto the blade roots of stator blades 12a and 12b are lixedly secured.
  • the tips of the rotor and stator blades are spaced a suiiicient distance from the housing l0 and hub 13, respectively, so as to insure clearance therebetween during operation of the compressor.
  • reaction and impulse blades Lia and lll are situated in a diverging passage defined by a section of the inner wall of the housing i9.
  • the len-.4ling edges of the reaction blades lla and Za are inclined towards the direction of the approaching fluid, and effect a deflection of the same by an amount comparable with that produced by conventional blade rows.
  • the present invention dillers from previous practice by the introduction in each stage of the additional blade rows lb and i212, forming additional impulse rotors and stators respectively.
  • the .unction of the impulse blade rows is to reverse the circumferential component of fluid velocity at the exit from the moving and stationary blades rcspectively.
  • stator blade row l2 is substantially identical to the rotor blade row lll (i.e. a mirror image thereof) substantially equal pressure rises are effected in the rotor and stator sections of each stage of the compressor (i.e. reaction blading).
  • the number of flow reversing lades 11b is shown to be equal to the number of reaction blades 11a; however, this need not be the case nor desired under all operating conditions. Accordingly, as illustrated in FlGURE 4, there are twice as many impulse blades 1lb and Z/J in the impulse sections as there are blades 11a and lla in the reaction sections.
  • the rotor section might be designed to include a single row of pure impulse or ow reversing blades 11b.
  • the single impulse rotor blade row effects the deflection of the gas while simultaneously producing ⁇ a substantial increase in the kinetic energy thereof.
  • the resulting static pressure rise during the subsequent passage of the gas ⁇ ilow through the reaction blades 12a of the stator blade row yields an even greater amount of stage work than with the previously described embodiments.
  • the operational description which is applicable to either of 'the three embodiments, varying in accordance with the dilerences in the particular blading configuration, will be presented in conjunction with fthe single stage illustrated in FIGURE 2.
  • the gas ow enters the inlet guide valves or prewhirl valves (not shown) of the compressor with a given axial velocity.
  • the prewhirl blades impart a rotational component to the gas flow in a direction opposite to the direction of rotor rotation which is from left to right in PlGURE 2.
  • the gas exiting from the prewhirl blades enters the reaction stage of the rotor at an angle al, which is designated as a positive angle for purposes of illustration.
  • the reaction rotor blades da deliect the gas ow through a rather small angle and the gas leaves the reaction section at an exit angle a2, which is also positive but somewhat smaller' in magnitude than the angle al.
  • the gas tlow exiting the reacting section of the rotor blades enters the impulse section.
  • the impulse rotor blades lib elect the deflection of the gas tlow through an angle of zero degrees so that the angle a3 at which the gas exits from the impulse section is substantially equal in magnitude but opposite to a2 as measured from the axis of rotation.
  • the stator blade row which includes the reaction blades 12a and ⁇ the impulse blades 12b, at an angle a4
  • the gas undergoes substantially the same deflections as occurred in the rotor blade row. Since in the illustrated embodiment symmetrical rotor and stator blade rows are utilized, the tangle a4 is numerically ⁇ equal to the ⁇ angle al but opposite in sign.
  • the rotor entry and exit angles have both been positive angles (i.e. the angles corresponding to ⁇ angles a1 and a3 in 'FIGURE 2.).
  • the entry angle a1 of the gas to the dual rotor blade row is positive while :the exit angle a3 is negative.
  • the -amount of work done by each stage i-s proportional to the numeral sum of the tangents of the angles al and a3.
  • a conventional axial flow compressor utilizing 50% reaction blading and with the rotor blades functioning at a speed of approximately'900 feet per second requires ⁇ seven stages to effect a certain degree of compression of a gas such as helium.
  • the gas emanating from -a compressor of .the conventional type has an exit angle yielding a positive exit swirl.
  • a specific embodiment of the compressor blade structure A which would be suitable for use in the example outlined above might preferably have a tip diameter of approximately 21/2 feet.
  • the pitch/ chord ratio might appropriately be chosen in the range of approximately .8 to 1.0, depending upon the turning angle desired and the stress considerations involved.
  • the tip/hub radius ratio of such a blading configuration might be chosen at approximately 1.4, this figure again being dictated by the particular application in which the bladin g is utilized.
  • a new and improved type of compressor blade structure which can effect the emcient compression of a gaseous fluid such as helium While utilizing a minimum number of compressor stages having rotor blade rows operating iat relatively low speed.
  • a blade structure is provided that is capable of being adapted for use in any number of other fluid circulating systems.
  • the blading structure contemplated by the present invention could be advantageously utilized in the free running turbo-compressor, which is disclosed and claimed in applicants copending application Serial No. 88,534, which was namelyd on February l0, 1961.
  • the neduction in blade speed that is realized with the blade structure hereinbefore described while the fluid is worked at substantially the same axial velocity makes this blading structure particularly suitable for this latter application.
  • an axial flow compressor a driven shaft, a housing surrounding the shaft that defines a passage for fluid flow therethrough and a blade structure which comprises (A) a rotor blade section and a stator blade section situated adjacent said rotor blade section in the direction of fluid flow;
  • said rotor blade section including (l) a first blade row containing a plurality of blades secured to and extending outwardly from said driven shaft in aligned circumferential spaced relation,
  • each of said blades having a tapered trailing edge and being positioned so that adjacent ones of said blades define diverging passageways which accommodate expansion of the fluid flow being circulated therethrough without effecting a substantial deflection thereof, and
  • each of said symmetrical blades having an enlarged central section and tapered leading and trailing edge sections inclined in the direction of shaft rotation
  • said symmetrical blades being positioned on said driven shaft in fixed relation to the blades of said first blade row so that the tapered leading edge of each of said symmetrical blades of said second blade row is aligned with the tapered trailing edge of the adjacent blade of said first blade row whereby the fluid flow exiting said first blade row of said rotor blade section is deflected through a substantial angle by the symmetrical blades of said second blade row without a corresponding pressure increase;
  • said stator blade section including (1) a first row of tapered blades and a second row of symmetrical blades that are secured to and extend inwardly from the inner wall of said housing adjacent said rotor blade row in the direction of liuid iiow,
  • the blades of said first and second stator blade rows being constructed and positioned on the inner wall of said housing so as to form a mirror image of said rotor blade rows.
  • a driven shaft In an axial flow compressor, a driven shaft, a housing surrounding the shaft that defines a passage for fluid flow therethrough and a blade structure which comprises (A) a rotor blade section and a stator blade section situated adjacent said rotor blade section in the direction of fluid flow;
  • said rotor blade section including (l) a first blade row containing a plurality of blades secured to and extending outwardly from said driven shaft in aligned circumferential spaced relation,
  • each of said blades having a tapered trailing edge and being positioned so that adjacent ones of said blades define diverging passageways which accommodate expansion of the fluid iiow being circulated therethrough without effecting a substantial deilection thereof, and
  • each of said symmetrical blades having an enlarged central section and tapered leading and trailing edge sections inclined in the direction of shaft rotation
  • said second blade row also including a plurality of symmetrical blades at least one of which is positioned between each pair of said symmetrical blades that are aligned with the blades of said first blade row;
  • said stator blade section including (1) a first row of tapered blades and (2) a second row of symmetrical blades that are secured to and extend inwardly from the inner wall of said housing adjacent said rotor blade row in the direction of lluid tiow,
  • an axial ilow compressor a driven shaft, a housing surrounding the shaft that denes a passage for fluid ilow therethrough and a blade structure which comprises (A) a rotor blade section and a stator blade section situated adjacent said rotor blade section in the direction of tiuid flow;
  • said rotor blade section including (l) at least one blade row containing a plurality of symmetrical yblades secured to said driven shaft for rotation therewith,
  • each of said symmetrical blades having an enlarged central section and tapered leading and trailing edges inclined in the direction of shaft rotation so that the fluid iiow passing therethrough is deflected through a substantial angle without a corresponding pressure increase;
  • said stator blade section including (l) a lirst blade row containing a plurality of tapered blades that extend inwardly from the inner wall of said housing in aligned spaced relation so that adjacent ones of said tapered blades deline diverging passageways which accommodate expansion of the iuid liow being circulated O o therethrough after exiting said rotor blade scction and (2) a second blade row of symmetrical blades extending inwardly irom said housing,
  • each of said symmetrical blades having an enlarged central section and tapered leading and trailing edge sections inclined in a direction opposite to that of shaft rotation and positioned adjacent said first blade row so that a pressure rise and a deflection of the fluid flow are sequentially effected during passage thereof through said stator blade section after exiting said rotor blade section.
  • a driven shaft in an axial tlow compressor, a driven shaft, a housing surrounding the shaft that defines a passage for iluid flow therethrough and a blade structure which comprises (A) a rotor blade section and a stator blade section situated adjacent said rotor blade section in the direction of iluid liow;
  • said rotor blade section including (1) at least one blade row containing a plurality of symmetrical blades secured to said driven shaft for rotation therewith,
  • each of said symmetrical blades having an enlarged central section and tapered leading and trailing edges inclined in the direction of shaft rotation so that the fluid flow passing therethrough is deflected through a substantial angle without a corresponding pressure increase;
  • said stator blade section including (l) a first blade row containing a plurality of tapered blades that extend inwardly from the inner wall of said housing in aligned spaced relation so that adjacent ones of said tapered blades define diverging passageways which accommo date expansion of the tluid ilow being circulated therethrough after exiting said rotor blade section and (2) a second blade row of symmetrical blades ertending inwardly from said housing,
  • said second blade row including at least twice the number of blades as are cmployed in said first blade row
  • each of said symmetrical blades having an enlarged central section and tapered leading and trailing edge sections inclined in a direction opposite to that of shaft rotation and positioned adjacent said first blade row so that a pressure rise and a deflection of the iiuid iow are sequentially effected during passage thereof through said stator blade section after exiting said rotor blade section.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US121875A 1961-07-05 1961-07-05 Compressor blade structure Expired - Lifetime US3112866A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US121875A US3112866A (en) 1961-07-05 1961-07-05 Compressor blade structure
GB25533/62A GB951713A (en) 1961-07-05 1962-07-03 Improvements in or relating to compressors
CH807062A CH428071A (de) 1961-07-05 1962-07-05 Schaufelung eines Axialströmungskompressors
DE19621428098 DE1428098A1 (de) 1961-07-05 1962-07-05 Verdichterbeschaufelung fuer Axialverdichter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US121875A US3112866A (en) 1961-07-05 1961-07-05 Compressor blade structure

Publications (1)

Publication Number Publication Date
US3112866A true US3112866A (en) 1963-12-03

Family

ID=22399293

Family Applications (1)

Application Number Title Priority Date Filing Date
US121875A Expired - Lifetime US3112866A (en) 1961-07-05 1961-07-05 Compressor blade structure

Country Status (4)

Country Link
US (1) US3112866A (de)
CH (1) CH428071A (de)
DE (1) DE1428098A1 (de)
GB (1) GB951713A (de)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3775023A (en) * 1971-02-17 1973-11-27 Teledyne Ind Multistage axial flow compressor
US3867062A (en) * 1971-09-24 1975-02-18 Theodor H Troller High energy axial flow transfer stage
US3877835A (en) * 1973-07-13 1975-04-15 Fred M Siptrott High and low pressure hydro turbine
US3937592A (en) * 1973-05-30 1976-02-10 Gutehoffnungshutte Sterkrade Aktiengesellschaft Multi-stage axial flow compressor
US5486091A (en) * 1994-04-19 1996-01-23 United Technologies Corporation Gas turbine airfoil clocking
EP0953728A1 (de) * 1998-04-27 1999-11-03 Kawasaki Jukogyo Kabushiki Kaisha Hilfskompressor mit Tandembeschaufelung
US6511285B2 (en) * 2001-06-20 2003-01-28 Rolls-Royce Plc Tandem guide vanes
DE10260153A1 (de) * 2002-09-27 2004-04-08 Delta Electronics, Inc. Lüfter für eine axiale Strömung mit Mehrsegmentblättern
US20060182626A1 (en) * 2004-11-04 2006-08-17 Del Valle Bravo Facundo Axial flow supercharger and fluid compression machine
US20080063522A1 (en) * 2006-09-07 2008-03-13 Rolls-Royce Plc Array of components
US20090317237A1 (en) * 2008-06-20 2009-12-24 General Electric Company System and method for reduction of unsteady pressures in turbomachinery
US20110189003A1 (en) * 2009-03-19 2011-08-04 Mitsubishi Heavy Industries, Ltd. Gas turbine
US20120070267A1 (en) * 2010-09-16 2012-03-22 Hitachi, Ltd. Axial Flow Compressor, Gas Turbine System Having the Axial Flow Compressor and Method of Modifying the Axial Flow Compressor
US20150152879A1 (en) * 2013-11-29 2015-06-04 Applied Thermal/Fluid Analysis Center Limited Liability Company Blade structure of axial fan
US10337519B2 (en) * 2015-11-24 2019-07-02 MTU Aero Engines AG Method, compressor and turbomachine
CN113309729A (zh) * 2021-07-29 2021-08-27 中国航发上海商用航空发动机制造有限责任公司 多级轴流压气机试验监测方法及装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4981414A (en) * 1988-05-27 1991-01-01 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
DE19525699A1 (de) * 1995-07-14 1997-01-16 Bmw Rolls Royce Gmbh Tandem-Schaufelgitter

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR811104A (fr) * 1936-09-08 1937-04-07 Compresseur rotatif aérodynamique
FR876380A (fr) * 1940-12-09 1942-11-04 Brown Compresseur axial avec turbine de récupération
FR982027A (fr) * 1943-06-01 1951-06-04 Perfectionnement aux compresseurs axiaux
US2699319A (en) * 1949-12-02 1955-01-11 Chrysler Corp Power conversion machine
GB780240A (en) * 1955-09-19 1957-07-31 Frederick Eggleton Improvements in or relating to the construction of axial flow turbines or compressors
US2931563A (en) * 1955-09-19 1960-04-05 Eggleton Frederick Construction of axial flow compressors

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR811104A (fr) * 1936-09-08 1937-04-07 Compresseur rotatif aérodynamique
FR876380A (fr) * 1940-12-09 1942-11-04 Brown Compresseur axial avec turbine de récupération
FR982027A (fr) * 1943-06-01 1951-06-04 Perfectionnement aux compresseurs axiaux
US2699319A (en) * 1949-12-02 1955-01-11 Chrysler Corp Power conversion machine
GB780240A (en) * 1955-09-19 1957-07-31 Frederick Eggleton Improvements in or relating to the construction of axial flow turbines or compressors
US2931563A (en) * 1955-09-19 1960-04-05 Eggleton Frederick Construction of axial flow compressors

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3775023A (en) * 1971-02-17 1973-11-27 Teledyne Ind Multistage axial flow compressor
US3867062A (en) * 1971-09-24 1975-02-18 Theodor H Troller High energy axial flow transfer stage
US3937592A (en) * 1973-05-30 1976-02-10 Gutehoffnungshutte Sterkrade Aktiengesellschaft Multi-stage axial flow compressor
US3877835A (en) * 1973-07-13 1975-04-15 Fred M Siptrott High and low pressure hydro turbine
US5486091A (en) * 1994-04-19 1996-01-23 United Technologies Corporation Gas turbine airfoil clocking
EP0953728A1 (de) * 1998-04-27 1999-11-03 Kawasaki Jukogyo Kabushiki Kaisha Hilfskompressor mit Tandembeschaufelung
US6350103B1 (en) 1998-04-27 2002-02-26 Kawasaki Jukogyo Kabushiki Kaisha Jet engine booster structure
US6511285B2 (en) * 2001-06-20 2003-01-28 Rolls-Royce Plc Tandem guide vanes
US7462014B2 (en) 2002-09-27 2008-12-09 Delta Eletronics, Inc. Axial flow fan with multiple segment blades
DE10260153A1 (de) * 2002-09-27 2004-04-08 Delta Electronics, Inc. Lüfter für eine axiale Strömung mit Mehrsegmentblättern
US20050095131A1 (en) * 2002-09-27 2005-05-05 Delta Electronics, Inc. Axial flow fan with multiple segment blades
US20060182626A1 (en) * 2004-11-04 2006-08-17 Del Valle Bravo Facundo Axial flow supercharger and fluid compression machine
US7478629B2 (en) * 2004-11-04 2009-01-20 Del Valle Bravo Facundo Axial flow supercharger and fluid compression machine
US20080063522A1 (en) * 2006-09-07 2008-03-13 Rolls-Royce Plc Array of components
US20090317237A1 (en) * 2008-06-20 2009-12-24 General Electric Company System and method for reduction of unsteady pressures in turbomachinery
US20110189003A1 (en) * 2009-03-19 2011-08-04 Mitsubishi Heavy Industries, Ltd. Gas turbine
US8734095B2 (en) * 2009-03-19 2014-05-27 Mitsubishi Heavy Industries, Ltd. Gas turbine
US20120070267A1 (en) * 2010-09-16 2012-03-22 Hitachi, Ltd. Axial Flow Compressor, Gas Turbine System Having the Axial Flow Compressor and Method of Modifying the Axial Flow Compressor
US9109461B2 (en) * 2010-09-16 2015-08-18 Mitsubishi Hitachi Power Systems, Ltd. Axial flow compressor, gas turbine system having the axial flow compressor and method of modifying the axial flow compressor
US20150152879A1 (en) * 2013-11-29 2015-06-04 Applied Thermal/Fluid Analysis Center Limited Liability Company Blade structure of axial fan
US10337519B2 (en) * 2015-11-24 2019-07-02 MTU Aero Engines AG Method, compressor and turbomachine
CN113309729A (zh) * 2021-07-29 2021-08-27 中国航发上海商用航空发动机制造有限责任公司 多级轴流压气机试验监测方法及装置

Also Published As

Publication number Publication date
DE1428098A1 (de) 1969-07-17
CH428071A (de) 1967-01-15
GB951713A (en) 1964-03-11

Similar Documents

Publication Publication Date Title
US3112866A (en) Compressor blade structure
US2689681A (en) Reversely rotating screw type multiple impeller compressor
US3824029A (en) Centrifugal supersonic compressor
US2313413A (en) Axial flow fan
US3173604A (en) Mixed flow turbo machine
US8137054B2 (en) Supersonic compressor
US3406632A (en) Reversible hydraulic apparatus
Day et al. The measurement and interpretation of flow within rotating stall cells in axial compressors
US2609141A (en) Centrifugal compressor
Dallenbach The aerodynamic design and performance of centrifugal and mixed-flow compressors
US2798661A (en) Gas turbine power plant apparatus
WO1986004970A1 (fr) Joint d'etancheite d'une turbo-machine
CN111550440A (zh) 一种径流式多级对转离心叶轮及其使用方法
US3292899A (en) Energy transfer machine
US3378229A (en) Radial flow turbine
US3010642A (en) Radial flow supersonic compressor
US2490066A (en) Diffuser
US3869220A (en) Rotary machines
US2438426A (en) Centrifugal compressor
US2527971A (en) Axial-flow compressor
US2505755A (en) Axial flow compressor
US3040971A (en) Methods of compressing fluids with centripetal compressors
CN112069619B (zh) 一种铅冷快堆核主泵的水力性能优化设计方法
US2965284A (en) Turbo-machine
US901228A (en) Turbo-pump.