US3773430A - Gas compressor - Google Patents

Gas compressor Download PDF

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Publication number
US3773430A
US3773430A US00235501A US3773430DA US3773430A US 3773430 A US3773430 A US 3773430A US 00235501 A US00235501 A US 00235501A US 3773430D A US3773430D A US 3773430DA US 3773430 A US3773430 A US 3773430A
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United States
Prior art keywords
rotor
chamber
mounting
housing
gas compressor
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
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US00235501A
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English (en)
Inventor
F Canova
M Hollow
L Krouse
H Hornschuch
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.)
Ingersoll Rand Co
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Ingersoll Rand Co
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Publication date
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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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage 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
    • F04D29/26—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
    • F04D29/322—Blade mountings
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • Single or multistage axial flow compressors could be especially useful for high density gases and in particular for gas pipeline applications where inlet pressures of 600-1200 psi are encountered, and process gas applications involving high inlet temperatures.
  • the axial flow compressor would have the following advantages as compared to centrifugal machines: a) higher efficiency potential, b) higher rotating speed, c) smaller physical size, and d) simpler and quicker rerating possibilities as only blade height and number of stages would have to be altered.
  • axial flow compressors for all the possible uses thereof, are limited in design however.
  • the present state of the art of axial flow compressors is inhibited because of the high bending loads which act on the rotating and stator blade systems.
  • these blade systems are of the conventional 50 percent reaction blading type such are used in most industrial and aircraft type axial flow machines.
  • the conventional 50 percent reaction blading axial flow compressors further, require an excessive stage length which warrants foreshortening that the overall machine length might be reduced, and also to facilitate the use of single rotor bearing and shaft seal arrangements, rather than two of each to accommodate the extendedly lengthy stages.
  • Another object of this invention is to set forth a gas compressor comprising a housing defining a compression chamber therewithin; said housing having means for admitting gas into said chamber and means for discharging compressed gas from said chamber; radially bladed rotor means for compressing gas within said chamber; shaft means rotatably mounting said rotor means within said chamber about an axis; vaned stator means within said chamber replaceably fixed to said housing and cooperative with said rotor means for compressing gas within said chamber; said chamber having an annular configuration and extending along said axis; wherein said rotor means extends coaxial with said stator means; and said shaft means support said rotor means at only one axial end of said rotor means, providing cantilevered mounting of said rotor means within said chamber; and further including means dispoed between said housing and at least one of said rotor, stator, and shaft means for isolating said rotor and shaft means from statically-induced distortions of said housing.
  • FIG. 1 is an axial view, partly in cross-section, of an embodiment of a gas compressor, according to the invention
  • FIG. 2 is an end view, in elevation, of the exit end of the FIG. 1 embodiment
  • FIG. 3 is an enlarged view of area A of FIG. 1;
  • FIGS. 4 and 5 are side and end views illustrative of the rotor blade and mounting ring arrangements
  • FIGS. 6 and 7 are side and plan views depicting the stator vane and mounting ring arrangements
  • FIGS. 8, 9, 10 and 11 diagrammatically compare the hub and tip cross-sections of stator vanes and rotor blades as known in prior art with those taught by the invention;
  • FIG. 12 is a schematic representation of the outside diameter of the rotor shaft extension, the diameter being generated from different radial centers and defining a plural-lobe surface;
  • FIGS. 13 and 14 depict an alternate embodiment of a gas compressor, according to the invention, the first being a partial, axial, cross-sectional view thereof, and the second being an enlarged view of area B of FIG. 13.
  • the novel gas compressor 10 comprises a housing 12 having a base 14 for supporting the housing thereupon.
  • a pair of oppositely disposed gas inlet flanges 16 are mounted to each side of the housing, the flanges defining inlet ports 18 which open on a chamber 20 defined within the housing.
  • a gas discharge flange 22 having an outlet port 24 formed therein.
  • a vaned stator 34 concentrically disposed about the rotor and shaft assembly, is mountedly supported within the compressor housing, by means of a cylindrical housing 36 which carries vane mounting rings 38 therewithin.
  • the stator 34 comprises a plurality of such vane mounting rings in juxtaposition, each of which has fixed therein a plurality of vanes 40.
  • All of the vanes 40 are of uniform length; however, the stator mounting rings 38 are of uniformly varying crosssection, from the inlet end to the outlet end of the compression chamber so that, toward the outlet end, progressively less of the vanes 40 protrudes into the compression chamber 30.
  • Each vane 40 is pinned into its respective mounting ring 38 and, further, each vane head 42 is set in an elastomer 44 for the purpose of damping vane vibration.
  • the housing base 14 comprises a vertical plate 46 which has passageways (not shown) formed therein for the admittance of ambient atmosphere as a sealant and also for introducing lubricating oil. Also, the lubricating oil is conducted by drilled passageway 48 from annular seals 50,500 set about the shaft of the rotor and shaft assembly 28 and subsequently drains into the bearing housing assembly.
  • the rotor and shaft assembly 28 comprises a plurality of juxtapositioned blade mounting rings 52, each of the rings having a plurality of the blades 32 mounted therein and radially extending away therefrom.
  • Each blade 32 at the head end thereof has a forked extension 54 which is bored through to receive a pin 56.
  • each blade mounting ring has a plurality of boreholes 58 formed therethrough for retaining opposite ends of the blade-retaining pins.
  • Each blade, at the head end thereof has a laterally extending tang 60 which protrudes into a complementary, interfacing recess 62 provided therefor in an adjacent blade head end.
  • the forked extensions 54 of adjacent blades have cooperative, arcuate cut-outs 64 formed therein with an elastomeric insert 66 therebetween.
  • the pinning of the forked extensions, and the elastomeric inserts, cooperate to allow the blades to swing through a small arc to accommodate for vibration.
  • the rotor shaft has a hollow extension 68 about which the rotor blade mounting rings 52 are mounted and, in cross-section, the shaft extension defines a mu]- ti-lobed circumference 70.
  • three lobes are defined by three arcs A, B, C of substantially 120, of common length and radius, but generated from three difierent, respective loci A, B, C.
  • a diffuser shell 72 which is open at both, opposite, ends. One end is in direct open communication with the outlet end of the compression chamber 30, and the end opposite opens directly onto the outlet port 24.
  • One end, the outlet end of this diffuser shell is retained by a circumferential shoulder 74 formed within the outlet flange and about the outlet port.
  • the diffuser shell outlet end and the circumferential shoulder have a compliant, sealant medium 76 therebetween.
  • the compressor housing has a radially and inwardly extending weldment 78 which abuttingly receives a radial ring 80 formed about and extending from the diffuser shell, said weldment and ring having an O-ring seal 82 therebetween.
  • Another ring 84 is welded within the outlet end of the housing, intermediate the weldment 78 and the outlet end of the diffuser shell 72, to present a flat-surfaced annulus for slidably supporting the diffuser shell therewithin.
  • Four ribs 86 (only one is shown), equally spaced therebetween about the rotor axis, are fixed at either ends thereof to the annulus of ring 84 and the weldment 78 to provide further support for the diffuser shell therewithin and for the outlet end of the compressor.
  • the blade mounting rings 52 of the rotor, and the vane mounting rings 38 of the stator as well, are each independently replaceable.
  • the innermost blade mounting ring i.e., the one nearest the inlet end of the compression chamber
  • the innermost blade mounting ring is set up against a circumferential shoulder 88 formed in the outer surface of the rotor shaft extension 68.
  • Successive adjacently-disposed blade mounting rings 52 are set against the innermost one, along the shaft axis.
  • the last or outermost blade mounting ring is secured on the rotor shaft extension by a retainer plate 90 bolted (by means not shown) to the shaft extension.
  • the vane mounting rings 38 of the stator similarly are set one against the one adjacent thereto, with the innermost one set against a radial shoulder 92 formed in a cylindrical stator housing 94.
  • the outermost vane mounting ring is secured in position by means of a bistepped retainer ring 96.
  • One step 98 of the retainer ring abuttingly receives the outlet end of the stator housing 94, and the retainer ring is secured to said stator housing thereat.
  • the other step 100 of the retainer ring being disposed on a face of the ring opposite the first-mentioned step, abuttingly receives the inlet end of the diffuser shell 72.
  • O-ring seals are disposed in both steps to fluid seal the joints formed thereat with the abutting components.
  • the novel gas compressor comprises means for counteracting axially-directed thrust of the rotor in which the rotor itself, in cooperation with the housing, provides such means.
  • the rotor has a radially extending web 102 formed thereon at the inlet end.
  • the housing vertical plate 46 presents a recess 104 in which the web rotates.
  • An annular, leakage access path 106 formed between a vertical plate shield 108 and the innermost rotor blade admits ambient-pressure gas to one side of the web 102.
  • Another annular, leakage access path formed between the rotor blade mounting ring retainer 90 and an inner cone 110 of the diffuser admits pressured gas to the hollow end 112 of the shaft extension 68.
  • the extension is drilled through, substantially axially, to conduct the leakage pressured gas through a passageway 114 there provided to the vertical plate recess 104. Accordingly, the web 102 encounters compressor inlet pressure on one side thereof the side from which direction thrust is effected, and outlet gas pressured on the other side thereof to counteract the thrust. The web 102 engages a labyrinth seal 116, on the circumferential surface thereof, to seal between the disparate pressures.
  • the invention teaches the use of turbine-nozzle-type vanes in the stator.
  • typical, prior art 50 percent reaction blading requires a stage length of approximately 3.075 inches.
  • turbine-nozzle-type stator vanes as shown in FIGS. 10 and 11, a substantially twenty per cent reduction of stage length (i.e., to approximately 2.55 inches) is realized. It is this teaching which makes it possible to have a great plurality of stages 10 being shown in FIG. 1, by way of example, in the first embodiment in a relatively short gas compressor axial dimension. Further, this teaching makes possible the rotary support of the numerous stages of rotor blades and the shaft therefor by means of a single bearing housing at only one end of the shaft.
  • the gas flow through the rotor blades 32 is oriented in the exit direction.
  • no guide vanes are required 1 at the entrance to the exit diffuser.
  • the diffuser itself is simplistic and efficient, the same defining a long, conical annulus devoid of obstructive ribs or struts.
  • the novel compressor due to the independent replaceability of the vane and blade mounting rings 38 ,,and 52, renders maintenance and repair easy, and accommodates a facile re-rating of the compressor. Simply by replacing given outermost mounting rings with dummy rings or spacers, or by wholly substituting differently-dimensioned and/or configured vanes and blades in replacement mounting rings, the performance of the compressor can be altered.
  • the alternate compressor embodiment is quite similar to the first, excepting that the gas inlet and outlet arrangement, and gas compressing direction, are reversed.
  • the conical annulus 118 comprises the gas inlet, and the compression chamber 120 narrows toward the axial end thereof which is opposite the inlet.
  • a side-mounted flange port 122 (only one being shown) comprises the compressed gas outlet.
  • the thrust counteraction is effected in this embodiment by the admittance of the pressured gas through a passageway 124 formed in the rotor shaft extension for impingement thereof against a pressure plate 126 fixed within the cone 128 of the conical annulus.
  • a housing defining a compression chamber therewithin
  • said housing having means for admitting gas into said chamber and means for discharging compressed gas'from said chamber;
  • vaned stator means within said chamber replaceably fixed to said housing and cooperative with said rotor means for compressing gas within said chamber;
  • said chamber having an annular configuration and extending along said axis; wherein said rotor means extends coaxial with said stator means;
  • said shaft means support said rotor means at only one axial end of said rotor means, providing cantilevered mounting of said rotor means within said chamber; and further including means disposed between said housing and at least one of said rotor, stator, and shaft means for isolating said rotor and shaft means from staticallyinduced distortions of said housing; wherein said rotor means includes means cooperative with said housing for counteracting axially-directed thrust of said rotor means; and
  • said thrust counteracting means comprises a web, having first and second oppositely disposed bearing surfaces, formed on one axial end of said rotor means, and conduit means, formed in said rotor means, communicating said discharge means and compressed gas issuing therethrough with said first bearing surface; wherein said web is disposed in a recess formed in said housing; and further comprises a passageway formed in said housing which communicates said second bearing surface with the atmosphere and means sealing between said conduit means and said passageway.
  • a gas compressor according to claim 1, wherein:
  • said discharging means includes a diffuser having an annular configuration extending coaxial with said given axis and a uniformly varying and unobstructed cross-section from one axial end thereof to the other.
  • a gas compressor according to claim 1, wherein:
  • said web extends radially from said one axial end of said rotor.
  • a gas compressor according to claim 1, wherein:
  • said stator means comprises a cylindrical member enveloping said chamber
  • said member having an inwardly-directed, radial shoulder formed on one end thereof, and a uniform-diameter, cylindrical, mounting surface extending from said shoulder to the end of said member which is opposite said one end;
  • a plurality of vane mounting rings disposed in juxtaposition upon and about said mounting surface, a first one of said mounting rings being set against said radial shoulder, others thereof being set out from said first one, successively, along said axis, toward said opposite end;
  • said cylindrical member having an annular recess formed therein at said opposite end;
  • a gas compressor according to claim 4, wherein:
  • each vane mounting ring of said plurality thereof is of discrete cross-sectional dimension.
  • a gas compressor according to claim 5, wherein:
  • said vane mounting rings, and the discrete crosssectional dimensions thereof, cooperate with said rotor means to define said chamber with a varying cross-section from one axial end thereof to the other.
  • a gas compressor according to claim 4, wherein:
  • each of said vane mounting rings is independently replaceable from said cylindrical member.
  • vanes of each plurality thereof have ends thereof fixed in their respective vane mounting ring; and said stator means further comprises means securing said vane ends in said respective vane mounting rings, and means for resiliently enveloping said vane ends and damping said vanes against vibration.
  • a gas compressor according to claim 4, wherein:
  • vanes have a cross-sectional configuration which conforms with a turbine nozzle cross-sectional configuration, comprising a thick, bulbous inlet section, a markedly arcuate mean camber line, and a chord line, a greater portion of which lies external of said vane cross-section.
  • a gas compressor according to claim 1, wherein:
  • said rotor means comprises pluralities of rotor blades
  • said stator means comprises pluralities of stator blades, said rotor and stator blades being cooperative to define a plurality of successive compressing stages along said axis, from an inlet end to an outlet end of said compression chamber;
  • each of said stages encompasses an axial length of not more than 2.55 inches.
  • a gas compressor according to claim 10,
  • said discharging means comprises a diffuser having an inlet and an outlet
  • said inlet of said diffuser opens directly, in immediate adjacency thereto, onto the outermost and last compressing stage.
  • a gas compressor comprising:
  • a housing defining a compression chamber therewithin
  • said housing having means for admitting gas into said chamber and means for discharging compressed gas from said chamber;
  • vaned stator means within said chamber replaceably fixed to said housing and cooperative with said rotor means for compressing gas within said chamher;
  • said chamber having an annular configuration and extending along said axis; wherein said rotor means extends coaxial with said stator means;
  • said shaft means support said rotor means at only one axial end of said rotor means, providing cantilevered mounting of said rotor means within said chamber; and further including means disposed between said housingand at least one of said rotor, stator, and shaft means for isolating said rotor and shaft means from staticallyinduced distortions of said housing, wherein said rotor means comprises a shaft extension coupled to said shaft means; said shaft extension comprising a cylindrical member which, in cross-section, defines a plural-lobe periphery, all lobes of said periphery being of common curvature and length, and each curvature of each lobe defining an are generated from a radial locus distinct from the radial loci of the other arcs of the other lobes.
  • a gas compressor according to claim 12, wherein:
  • said shaft extension in cross-section, defines a threelobe periphery; and said rotor means further comprises a plurality of blade mounting rings disposed in juxtaposition upon and about said periphery; pluralities of blades; and means mounting a plurality of blades to each of said blade mounting rings.
  • a gas compressor according to claim 15, wherein:
  • each of said blades has a mounting head on one end thereof which defines a bifurcation; said mounting heads and said blade mounting rings have boreholes formed therethrough; and said mounting means comprises pins in penetration of said boreholes for securing said blades to said blade mounting rings and for accommodating slight pivotal movement of said blades about said pins.
  • a gas compressor according to claim 14, wherein:
  • said mounting heads each have a laterally extending tang formed on one side thereof and a tangreceiving recess formed in the side thereof opposite said one side, for effecting a contacting interengagement of each mounting head with a mounting head adjacent thereto; and said mounting heads each have arcuate cut-outs formed on said one and said opposite sides; and further including elastomeric inserts disposed in said cut-outs, between each of said mounting heads, for cooperation with said pins to provide for vibration-damping of said blades.

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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)
  • Rotary Pumps (AREA)
US00235501A 1972-03-17 1972-03-17 Gas compressor Expired - Lifetime US3773430A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US23550172A 1972-03-17 1972-03-17

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US3773430A true US3773430A (en) 1973-11-20

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US00235501A Expired - Lifetime US3773430A (en) 1972-03-17 1972-03-17 Gas compressor

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US (1) US3773430A (it)
JP (1) JPS4913711A (it)
AU (1) AU462996B2 (it)
BE (1) BE796869A (it)
CA (1) CA977281A (it)
DE (1) DE2312067A1 (it)
FR (1) FR2177318A5 (it)
GB (4) GB1408615A (it)
IT (1) IT982514B (it)
NL (1) NL7303761A (it)
ZA (1) ZA73561B (it)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3865504A (en) * 1972-09-08 1975-02-11 Bbc Sulzer Turbomaschinen Axial compressor
US3918832A (en) * 1974-07-29 1975-11-11 United Technologies Corp Stator construction for an axial flow compressor
EP1375822A2 (en) 2002-06-25 2004-01-02 Hitachi, Ltd. Gas turbine production process

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2453294A1 (fr) * 1979-04-04 1980-10-31 Snecma Dispositif de fixation d'aubes sur un rotor de compresseur pour turbo-reacteur
DE2946297C2 (de) * 1979-11-16 1986-08-07 Mbk Maschinenbau Gmbh, 7964 Kisslegg Maschine zur Herstellung von Bewehrüngskörpern für Betonrohre
JPS5688501A (en) * 1979-12-21 1981-07-18 Matsushita Electric Ind Co Ltd Heater
CN110005644B (zh) * 2018-01-04 2021-07-30 中国航发商用航空发动机有限责任公司 带中间机匣的轴流压气机静子

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB572859A (en) * 1942-04-03 1945-10-26 Armstrong Siddeley Motors Ltd Mounting the blades of axial-flow, rotary compressors or turbines
US2410769A (en) * 1941-05-07 1946-11-05 Vickers Electrical Co Ltd Turbine, turbine type compressor, and the like rotating machine
GB814809A (en) * 1954-10-22 1959-06-10 Maschf Augsburg Nuernberg Ag Improvements in or relating to axial-flow turbines employing hot propellant media, especially gas turbines
GB866793A (en) * 1956-09-01 1961-05-03 Gio Batta Sommariva Improvements in or relating to axial flow compressors

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410769A (en) * 1941-05-07 1946-11-05 Vickers Electrical Co Ltd Turbine, turbine type compressor, and the like rotating machine
GB572859A (en) * 1942-04-03 1945-10-26 Armstrong Siddeley Motors Ltd Mounting the blades of axial-flow, rotary compressors or turbines
GB814809A (en) * 1954-10-22 1959-06-10 Maschf Augsburg Nuernberg Ag Improvements in or relating to axial-flow turbines employing hot propellant media, especially gas turbines
GB866793A (en) * 1956-09-01 1961-05-03 Gio Batta Sommariva Improvements in or relating to axial flow compressors

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3865504A (en) * 1972-09-08 1975-02-11 Bbc Sulzer Turbomaschinen Axial compressor
US3918832A (en) * 1974-07-29 1975-11-11 United Technologies Corp Stator construction for an axial flow compressor
EP1375822A2 (en) 2002-06-25 2004-01-02 Hitachi, Ltd. Gas turbine production process

Also Published As

Publication number Publication date
NL7303761A (it) 1973-09-19
GB1408617A (en) 1975-10-01
CA977281A (en) 1975-11-04
JPS4913711A (it) 1974-02-06
GB1408618A (en) 1975-10-01
IT982514B (it) 1974-10-21
FR2177318A5 (it) 1973-11-02
GB1408615A (en) 1975-10-01
DE2312067A1 (de) 1973-09-27
AU4844872A (en) 1974-05-02
GB1408616A (en) 1975-10-01
ZA73561B (en) 1973-11-28
BE796869A (fr) 1973-07-16
AU462996B2 (en) 1975-07-10

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