US2611532A - Turbine driven compressor - Google Patents

Turbine driven compressor Download PDF

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US2611532A
US2611532A US618042A US61804245A US2611532A US 2611532 A US2611532 A US 2611532A US 618042 A US618042 A US 618042A US 61804245 A US61804245 A US 61804245A US 2611532 A US2611532 A US 2611532A
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Prior art keywords
turbine
compressor
blade
shaft
wheels
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Ljungstrom Birger
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Saidcombustion gases may be utilized either for the propelling of aeroplanes, projectiles, ships or carriages according-to the reaction principle or for driving another gas turbine in which the dynamically available energy of the combustion gases as delivered from said first-mentioned turbine .is utilized for, driving a power shaft or shafts.
  • Said last-mentioned turbine hereinafter re ferred to as the power turbine, especially when it is desired to obtain a compact plant, may be arranged as a direct continuation of the driving turbine of the compressor, or it may comprise a separate machine, the gas inlet of which communicates with the combustion gas outlet of the first turbine.-'
  • the power turbine ' may be situated coaxially outside the'fir'st turbine in the outlet of an additional combustion chamber located between the two turbines;
  • the rotary "machines 'with -'as-- sociated combustion chambers may be assembled so as to form a ci-rculation system.
  • the combined compressor and drivingturbine therefor comprises three main parts, comprising two rotary engines or machines, namely a gas turbine and a turbine type of compressor, both of multi-stage type, and a shaft system provided therebetween, which comprises. a set of tubular shafts concentrically surrounding each other and rotatable independently of each other, and in whichi'ach tubularlshaft is connected at one end to blade wheeljlior wheels) of the turbine and at the other end (or wheels) of the compressor.
  • V v w The above said shaft system DQrmits-tr'ans:
  • the proportions of this blade wheel may be applied to all sizes of wheel of one and the same engine or machine, provided the dimensions of the various wheels are selected in proper progression and all of them rotate'at the same peripheral speed.
  • the centrifugal force, the efiiciency, the maximum output of, power, and the speed of flow of the driving fluid may in such case be made substantially equal for all blade wheels, irrespective of such changes of pressure and/or volume as may occur-during sumptionand increasesT the radius of action.
  • theinvention allows the connection of any or all of the tubular shafts-at one end or both'to more than one blade wheel, say two or three, or to different numbers of blade wheels at opposite ends.
  • Sucha modification reduces the number of tubular shafts required for a givennumber of blade wheels, but, on the other hand, reduces the possibility of obtaining a maximum "output from each blade ring, and causes a corresponding increase of theweight ofthe rotary system.
  • the most eificient way in which to use the invention is to connect the tubular shafts to but a single blade wheel at either end.
  • every second blade wheel of the turbine and the compressor rotates in one direction and the remaining blade wheels in the opposite direction so that adjacent blade wheels of one and thesame engine or machine always rotate inopposite directions.
  • the angles of blade. are selected so as to allowthe driving fluid to pass from'one blade wheel to another without the aid of guide blades inserted thereshaft, and to correspondingly reduce; the. damn-' sions of the plant as a whole; The reduction of the weightreduces, especially in 'cas'e of an ae'roplanewthe power andl-fuel com.
  • Invested in a larger plant the reduction of the weight may be utilized either to obtain a higher speed or a higher efficiency.
  • Fig. 1 illustrates the invention as embodied in a machine for driving an aeroplane according to the reaction principle.
  • Fig. 1 shows a diagrammatic axial section of the machine.
  • Fig. 2 is a side elevation, partly in axial section, of one end of the shaft system of said machine.
  • Figs. 2A and 2B are detail views of means for locking and sealing blade wheels on shafts.
  • Figs. 3-6 are detail sectional views showing the attachment of the blades to the blade wheels.
  • Fig. 7 is a section of the attachment of a blade on a larger scale.
  • Fig. 8 shows a form of blade roots.
  • Fig. 9 is a diagrammatic side view of the .power plant as inserted in the wing of an aeroplane.
  • Fig. 10 is a front view of said wing and plant.
  • Fig. i1- isa side elevationpf atubularshait system.
  • Figs.12 and 13 are diagrammaticviews ofpower plants, the turbine and compressor of which are providedwith cylindricalcasings.
  • Fig. 14 is a-diagrannnat-icpart; sectional side elevation of; an; embodiment; of the invention including besides the compressor and associated driving turbine a powerturbine.
  • Fig. 15 is adiagrammaticview-of the invention as embodied in a circulation system.
  • Fig. 1 the powerplant is shown as located at the, rear end of an aeroplane, the-arrangement being such as to allow a'readydismantling of the power plant.
  • the power plant illustrated in this figure includes in- ,addition to the three main; parts above. stated a, combusticn chamber located between the turbine and the compressor and another. chamber provided 'inth'e outlet of the turbine which is adapted'for effecting a 'recombustion, for instancetoallow agforced operation. Since the combustion means do not form part of this invention, they are not shown inthe drawingzthey may beassumed to-be of well-known design. 7
  • the power plant shown has no power shaft; the delivery of power being effected exclusively by reactionin the turbine outlet.
  • an oil mist lubricating system particularly-in caseof a shaft system mounted in ball bearing.
  • :Inthis-connection-an auxiliaryhigh pressure fan blower-is provided which-takes its air from :the. combustion chamber located immediately behind the compressor through separate pipesrthefiattenedsections of which-9 :05am: inle o theicompressor in order to form ,a .cooling; device; for the: air withdrawn which; is :thenpas d-thr u h an oil m st .1 1- bricating device or devices :placed in front; of tbeinl t of the iarrblowe I v
  • the said auxiliary; fan; blower 3' may 2 be idrivcn by. mean f toothed-eearinesfrom the first blade wheel of the compressor or in any; other; appropriate way.
  • I useras'tartin rmotor' preferably petrol :driven, provided with; an electric starting mechanism. Inserted between said 4 starting motor and the fan blower is a pawl and ratchet gear.
  • the first and the last blade wheels of the coinpressor and the turbine together with the respective tubular shaft are thus started by the action of the starting motor via the fan blower and the associated toothed gearing, thereby forcingthe-air. or driving fluid of the plant in axial direction through the acon' 'pressor, the combustion chamber and the turbine.
  • the combustion .process in the combustion chamber being simul- I taneously started, the plant as a whole is thus -sta-rted.- -Thestarting motor and its pawl and ratchet. gear man then be stopped.
  • therpower: plant comprises a number, say four, similar-nnits, placed in the wings of an aero- .plane,
  • thesystem, ,or the shafts may first be cylindricalto allow their insertion into each other and then conformedat their ends to the cross section: desired accordingasthe mounting is proseeding shaftby shaft from inside outwards.
  • desired accordingasthe mounting is proseeding shaftby shaft from inside outwards.
  • the fastening of the'blade wheels to the ends of the tubular shafts may be facilitated by thickening the walls of'the shaft ends by an amount corresponding to" the plays existing between entirelycylindrical-shafts;
  • the shaft endsbf-theassembled shaft system may be provided with separate stifiening pieces at their ends irrthe-fornr of bushingsattached by pressing or welding 'whichmay-either be provided with means] for "receiving .the' blade wheels or afterwards workedffor thesamepurpose.
  • each blade wheel is composed'of two axially abutting discs between which there is a space surrounded by walls the thickness of which decreases outwards like the thickness of an undivided blade wheel of conventional design.
  • Said novel structure of the blade wheels has for its purpose to permit a good cooling of the blade wheels so that their surfaces facing each other may be situated at a short distance apart and provided with labyrinth packings for cooling purposes.
  • the blade wheel structure above descri ed permits shaping and mounting the labyrinth packings with a view to obtaining both a balancing of the axial thrusts appearing between the blade wheels and a reduction of the quantity of lubricating oil and cooling fluid passing between the wheels of each pair of wheels.
  • the blade wheels have been assumed as rigidly connected to the tubular shafts against axial movements, it is evident, however, that they may be connected thereto by axially adjustable means, provided the axial position of the blade wheels with relation to each other is stabilized and maintained by the use of appropriate labyrinth packings subjected to axial pressure transmitted by the cooling fluid.
  • the flow of the cooling fluid from between the outer edges of the blade wheels to the driving fiuid passing between the blade rings serves an additional purpose, inasmuch as the cooling fluid prevents leakage of the driving fluid into between the blade wheels, that is, past the inner ends of the blades.
  • the turbine and compressor casings Support no guide blades or the like between the blade wheels.
  • special packing means of heat elastic kind are provided which may suit, independently of the casings, such changes of the radius of the rotary system, including the expansion and contraction of the turbine blades, as are due to sudden changes of load or to a quick starting.
  • a lagging of the expansion or contraction of the turbine and compressor casings resulting from said changes of temperature do not require any increased plays.
  • the packing means provided on the inside of th turbine and compressor casings comprise well known expansion elements.
  • I may use-the innermost, or central, rotary tubular shaft to support the surrounding shafts; To this end said innermost shaft should be mounted in bearings at both ends.
  • the power to drive the fan blower may be derived from one free end of said shaft.
  • the power plant is mounted in the rear end of the aeroplane body by means of a flange I.
  • the main parts of the plant comprise the inlet 2, the compressor 3 with associated casing 3b; the turbine 5 with associated casing 5b, a cylindrical wall 4b connecting the casings 3b and 5b which forms a combustion chamber 4, and an outlet 6.
  • Said members form together a unitary structure surrounding the tubular shaft system 1 supported by a central stationary shaft l2 which is guided at both ends by bushings 8 and 9 carried by or formed integrally with stationary guide blade wheels l6 and II provided at opposite ends of the compressor and turbine bladings, respectively.
  • the said 7 central shaft [2 supports ball bearings I3 and I 4 serving to guide the first pair of blade wheels l5, l6 and the associated tubular shaft l'l carrying said wheels.
  • the tubular shaft system shown in Fig. 1 comprises a set of rotary shafts l824, which may rotate at individual peripheral. speeds with adjacent shafts rotatin in opposite directions.
  • the blade wheels of the turbine connected to the shaft system which are numbered Ilia to 22a, and those of the compressor which are num bered [5b to 2Ib, are all mounted on ball bearings to permit independent rotation of each individual shaft.
  • the first and last ball bearings belonging to the compressor are shown at I 3 and 26, respectively, and the first and last ball bearings of the compressor are shown at 25 and 15, respectively.
  • the innermost ball bearings of the compressor and the turbine, namely 26 and 25, are supported by guide blade rings 28 and 21'andthe insulating bushing 29 inserted therebetween, in order that also the outermost tubular shaft 24 may be positively guided by the casing of the plant.
  • the tubular shaft system together with the blade wheels connected thereto is positively guided at its outer ends by the ball bearings l3 and I4 and in the middle of the system by the ball bearings 25 and 26 as already stated, whereas the ball bearings situated between l4 and 25 and between [3 and 26 are centered within the turbine and compressor casings respectively by the action of said first-mentioned bearings.
  • the cooling system of the power plant com prises means for withdrawing air from the combustion chamber 4 through pipes 30 symmetrically arranged around the plant, said pipes 36 passing through the air inlet 2 of the power plant in the form of flattened pipes 3
  • the fan blower forces the oil mist at an increased superpressure through the tubular shaft l2 into the centre of the shaft system along the entire length thereof.
  • the said high pressure fan blower is con-- nected by means of toothed gears 31 and 38 to a blade wheel I5 and is further connected by means of the pawl and ratchet gear'39 to v the starting motor which maybe provided with anelectric automatic starting device, not
  • numeral 1M indicates the entrance of the cooling' andLlubri'cating.oil mist into theispaces between. the various. tubular shafts, in whichzspacessaid :oil mistcmay be passed to the various rotary elements of the plant.
  • Fig. 2 isishown an axial section of one end ofthe shaft system including the stationary central pipe l2 and the rotary shafts i3 andl24.
  • both the guiding ball bearings is and 25 and thelother ball bearings which are situated .betweenthe-turbine disc to centre the turbinediscs land the rotaryshafts are shown.
  • the *turbineadiscs 1 8a andLZZa are fastened to the.- respective tubular' shafts i by being screwed on-thevthreaded'ends :thereof. Said threaded ends are of aigreater thickness than the remainder of the shafts.
  • the fastening of the turbine disc; 17a is also: effected by screwing, but in thiswcaseithe turbine dlsc'isnot in direct contact with the shaft end, inasmuch as asset of wedges 42 .of thin-sheet metal is inserted between the shaft iand-the turbine disc, said wedges being flexible, 'so .that Ithey may act as seals'for the locknut lS.
  • the bladeiwheel its illustrates another -modification in which the tubular shaft l8.is .providedwith a bushing 4 pushed thereon which isconnected' to the shaft bywelding, as indicatedatdb. Theconnection between the blade wheel and said bushing is efiected by meansof keysit and lock'nut t? with-associated washer 43.
  • Figs. 2A. and 2B show details of said tvzolastmentioned fastenings.
  • the abovesaid different ..fastening methods may be applied to all blade-wheels.
  • the second method requires mounting .of the hubs of the blade wheels subsequentto the introduction of the tubular shafts intoeach other, which prevents the shafts from being dismantled in the same way.
  • the cooling fluid may be in troduced-betweenall tubular shafts through a radial set of apertures,.while as shown at as the discharge of the lubricating fluid from between the tubular shafts may take place at axially displaced, points to the spaces between the blade wheels inside the-bearings thereof. As already indicated the cooling and lubricating fluid is then passed through the ball bearings radially outwards between. the blade whee1s,-as will be clear. from an inspection. of Fig. 3.
  • FIG. 1 shows anaxial section of two adjacent blade wheel discs bit-and 5327 with associated shaft end ball bearings.
  • labyrinth packings 5i and 52 situated at. radially spaced places adjacent theball .bearingsland the outer periphery of the discs, respectively.
  • labyrinth packingsJ may also be provided along the remainingportion of the opposite surfaces of the blade wheels.
  • the blade'wheels are each composed'of'twoaxiallyi'displaced discs 53 and 53b welded together at their inner and 'outer peripheries so .that they will constitute a hollow body the space of which is'indicated by the reference numeral 55.
  • the purpose of this construction has already :been pointed out hereinbefore.
  • the blades shown in Fig. may be fastened to their "respective "blade wheels by Welding, preferably resistance welding.
  • the blades are. fastened to oriormed integrally "with blade :roots 55- of special shape, as shown in Figs. 6, 7 and 8.
  • Fig. '7. illustratesthe fasteningmethod onallarger: scale. It is evident from the drawing that the caulking wire 56 causes a firm engagement at -51 as and for transmitting the centrifugal stresses and interconnecting the two discs 53 and 53b.
  • Eigsza and 5 show a .form of blade roots '55 havlnga thin radialweb EBprojecting from its inner surface said :web dueto its small thickness-having aigreatresistance to heat conduction thereby reducingathesamount of heat transmitted from .thebladesand the bladeroots to the blade wheel discs.
  • Fig. dillustrates .a .formcf tightening device provided on the-inside of. .the turbine .and compressor 'casings, which are adapted to prevent leakageofdriving. fluid beyond the tops of the blades or beyond .theouter-edges of the blade wheels.
  • said device consists of. axialprojections 59 at theinside of the conical casing 512. Asshown attic said axial projections may bereplaced by thin sheet metal rings of angular cross section, which are insorted in grooves formed inthe casing and sealed intoeengagement therewithby means of caulking wires 6!.
  • Fig.4 illustrates amorestructural form ofv device forwthe same purpose.
  • said .device comprises a: separate ringti connected by means of anexpansionring .63 to .a' seating ring 64 seatedin agroove-of the casing 5b and sealed in thishengagement by .means of a caulking wire 65.
  • This device allows an. independent contraction of the ring 62 with relation to the casing 522 due to changes of temperature and operation.
  • a vchannel-shaped ring 68 situated inside ringSZ which isprovidedatthe top of .the blade is formed with two tightening ridges which may be worn in operation with but little heat generation .until the play required by the operation is obtained.
  • Fig. Q shows a power plant according to the invention as located in the wing .ofan aeroplane. .Inthis case the-compressor 3 and theturbine'b arerconn'ected for-practical reasons to each other by means of a very long'tubular shaft system 6 1, the construction oflwhich is shown in'Fig; ll. Said shaft system.may be assumed to be constructed according to the principles above set forth.
  • Fig..10 the wing with thepowerplant therein is shown infront. elevation, the air inlet. opening being specially indicatedv and the entire structurelbeing. shaped .witha view to obtaining the smallest airresistance possible.
  • FIGs. -12 .and 13 are diagrammatic views of power. plants having. cylindrical instead of conical compressor K and-gas turbine T, .the diameters of both being either.equal,.as shown in Fig. 12, or different, asshowniin Fig. 13, withthediameter of the compressor considerably greater than that of the turbine.
  • the invention is described as applied to a power plant for the propelling of aeroplanes according to the reaction principle, It is to be noted, however, that the invention may be applied in other connections, where combustion gases, produced under a high pressure, are utilized, as for instance, for the propelling of projectiles, ships, carriages and so on as well as for stationary power generating purposes.
  • IOI designates a stationary guide blade ring provided at the inlet of the turbine type of compressor
  • I02 designates the blade wheels of said compressor.
  • the guide blade ring I M is connected at its outer periphery to the compressor casing I03 and at its inner periphery to a bearing I04 supporting the shaft I05 of the power turbine to be hereinbelow described.
  • the blade wheels I02 of the compressor are of diameters gradually decreasing from the inlet towards the outlet of the compressor.
  • Each blade wheel is supported by a tubular shaft I06 which carries at its other end a corresponding blade wheel I01 of a gas turbine.
  • the tubular shafts I06 are not shown to their entire extent in order not to render the illustration obscure but only their ends are shown.
  • the individual tubular shafts I 06 may rotate independently of each other.
  • ball bearings I08 are inserted between the blade wheels I 02 of the compressor, and similar ball bearings I09 are inserted between the blade wheels I01 of the turbine,
  • a stationary partition I I0 which projects outwards into a combustion chamber II I surrounding the compressor and turbine casings. Said partition forms a baflle which acts to guide tda driven shaft.
  • a single rotation power turbine of conventional type comprising a set of stationary guide blade rings H3 and a corresponding set of rotary blade -wheels H4.
  • the latter are connected to thesaidfirstmentioned shaft I 05 which is mounted at its one end in the bearing I04 above referred to and at its other end in a bearingllipositio'nedoutside the turbine II4, preferably-inconibinatlon with the outlet-thereof.
  • the shaft I05 carries a flange II 6 for its coupling
  • the exhaust gases expelled from the turbine H4 are discharged through the outlet II! to be then pas'sed, for instance, to a plant for recovering their heat content.
  • the gas turbine adapted todelivr'power through its shaft is mounted separately at a distance from the compressor and its driving turbine.
  • a combustion chamber'fI22"and1.in.front of the power turbine I23 is another combustion chamber I24.
  • the system also includes a heat exchanger I25. In order to render the insertion of the heat exchangers into the system more easily the compressor and its driving turbine are so related to each other that their outlets are facing each other.
  • the fluid to be compressed is drawn into the compressor as indicated by the arrows a and passes from the compressor through the heat exchanger I25 where its already very high temperature (say 300 C.), due to compression, is further increased (say to 450 C.) by the admission of heat from the gases discharged from the power turbine I23.
  • the fluid then enters at this high temperature the combustion chamber I22 where it is mixed with fuel and the mixture resulting is ignited.
  • the combustion gases produced which obtain a still increased temperature (say 900 C.) enter the driving turbine I2I of the compressor where they deliver part of their energy content under reduction of their pressure and temperature (say to 600 C.).
  • the gas expelled from the turbine I2I is not passed directly to the power turbine I23 but is first led through the combustion chamber I24 where fuel is added and combustion again established. This produces another increase of temperature up to the maximum value (say 900 C.), and the heat gases produced enter the power turbine I23 where their energy is transformed into Work delivered through the shaft I26.
  • the gases discharged from the turbine I23 maintain still a comparatively high temperature (say 500 C.) and are therefore passed through the heat exchanger I25 Where part of their heat content is recovered.
  • the remainder of the heat content corresponding, for instance, to a temperature of 350 0., may be utilized for water heating and/or similar purposes.

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  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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US618042A 1944-09-23 1945-09-22 Turbine driven compressor Expired - Lifetime US2611532A (en)

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Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2700935A (en) * 1948-04-27 1955-02-01 Bendix Aviat Corp Rocket fuel pump and the like
US2788951A (en) * 1951-02-15 1957-04-16 Power Jets Res & Dev Ltd Cooling of turbine rotors
US2839005A (en) * 1953-10-14 1958-06-17 Herbert E Means Turbine driven pump
US2842306A (en) * 1952-04-30 1958-07-08 Alfred Buchi Turbine driven multi-stage blower or pump
US2859935A (en) * 1951-02-15 1958-11-11 Power Jets Res & Dev Ltd Cooling of turbines
US2922278A (en) * 1948-11-30 1960-01-26 Szydlowski Joseph Coaxial combustion products generator and turbine
US2922618A (en) * 1956-03-06 1960-01-26 Gen Electric Turbo-machine rotor
US2927724A (en) * 1957-10-02 1960-03-08 Avro Aircraft Ltd Floating blade shrouds
US2929207A (en) * 1955-08-08 1960-03-22 Adolphe C Peterson Axial flow gas turbine
US2931563A (en) * 1955-09-19 1960-04-05 Eggleton Frederick Construction of axial flow compressors
US2937495A (en) * 1956-02-27 1960-05-24 Power Jets Res & Dev Ltd Gas turbine plant
US2990108A (en) * 1957-03-04 1961-06-27 Curtiss Wright Corp Compressor with annular discharge diffuser
US3023577A (en) * 1955-10-24 1962-03-06 Williams Res Corp Gas turbine with heat exchanger
US3037352A (en) * 1958-09-08 1962-06-05 Vladimir H Pavlecka Bypass jet engines using centripetal flow compressors and centrifugal flow turbines
US3157991A (en) * 1963-04-16 1964-11-24 Kemenczky Establishment Flow regulating device for jet propulsion engine
US3194011A (en) * 1962-04-23 1965-07-13 Paul W Chaney Aircraft with non-combustion air reaction engine
US3259195A (en) * 1962-04-23 1966-07-05 Paul W Chaney Aircraft with non-combustion, air reaction engine
US3302866A (en) * 1965-03-16 1967-02-07 Polytechnic Inst Brooklyn High velocity fluid accelerator
US3897986A (en) * 1972-12-08 1975-08-05 Rolls Royce 1971 Ltd Bearings
FR2506839A1 (fr) * 1981-05-27 1982-12-03 Onera (Off Nat Aerospatiale) Turboreacteur contra-rotatif simplifie
US6102655A (en) * 1997-09-19 2000-08-15 Asea Brown Boveri Ag Shroud band for an axial-flow turbine
WO2005021975A1 (de) * 2003-08-21 2005-03-10 Anton Niederbrunner Laufradanordnung einer strömungsmaschine
CN113153537A (zh) * 2021-03-19 2021-07-23 哈尔滨工业大学 一种应用于高超声速飞机的三轮冷却-制冷循环冷却系统

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190500372A (en) * 1905-01-07 1906-04-07 Henrik Van Meerten Improvements in or pertaining to Turbines.
FR411472A (fr) * 1910-01-11 1910-06-17 Emile Baptiste Merigoux Turbine pouvant fonctionner avec les mélanges détonants, la vapeur et autres fluides gazeux
AT51150B (de) * 1909-09-13 1911-12-11 Willibald Gelinek Mit einer Dampf-, Gas- oder dgl. Turbine vereinigter Kompressor.
US2080425A (en) * 1933-02-10 1937-05-18 Milo Ab Turbine
US2297508A (en) * 1940-02-29 1942-09-29 Schutte Alfred Rotor for turbines
FR879123A (fr) * 1941-01-10 1943-02-15 Perfectionnements aux tuyères thermo-propulsives et aux aéronefs et autres véhicules propulsés par ces tuyères
US2401826A (en) * 1941-11-21 1946-06-11 Dehavilland Aircraft Turbine
US2405164A (en) * 1941-03-25 1946-08-06 Northrop Aircraft Inc Turbine stator
US2411124A (en) * 1941-11-01 1946-11-12 Vickers Electrical Co Ltd Internal-combustion turbine plant
US2413225A (en) * 1941-05-14 1946-12-24 Rolls Royce Internal-combustion turbine
US2414551A (en) * 1941-07-21 1947-01-21 Northrop Aircraft Inc Compressor
US2430398A (en) * 1942-09-03 1947-11-04 Armstrong Siddeley Motors Ltd Jet-propulsion internal-combustion turbine plant
US2435990A (en) * 1945-08-17 1948-02-17 Westinghouse Electric Corp Gas turbine lubricating oil cooling and air inlet deicing system
USRE23198E (en) * 1950-02-21 Reaction propelling device for

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE23198E (en) * 1950-02-21 Reaction propelling device for
GB190500372A (en) * 1905-01-07 1906-04-07 Henrik Van Meerten Improvements in or pertaining to Turbines.
AT51150B (de) * 1909-09-13 1911-12-11 Willibald Gelinek Mit einer Dampf-, Gas- oder dgl. Turbine vereinigter Kompressor.
FR411472A (fr) * 1910-01-11 1910-06-17 Emile Baptiste Merigoux Turbine pouvant fonctionner avec les mélanges détonants, la vapeur et autres fluides gazeux
US2080425A (en) * 1933-02-10 1937-05-18 Milo Ab Turbine
US2297508A (en) * 1940-02-29 1942-09-29 Schutte Alfred Rotor for turbines
FR879123A (fr) * 1941-01-10 1943-02-15 Perfectionnements aux tuyères thermo-propulsives et aux aéronefs et autres véhicules propulsés par ces tuyères
US2405164A (en) * 1941-03-25 1946-08-06 Northrop Aircraft Inc Turbine stator
US2413225A (en) * 1941-05-14 1946-12-24 Rolls Royce Internal-combustion turbine
US2414551A (en) * 1941-07-21 1947-01-21 Northrop Aircraft Inc Compressor
US2411124A (en) * 1941-11-01 1946-11-12 Vickers Electrical Co Ltd Internal-combustion turbine plant
US2401826A (en) * 1941-11-21 1946-06-11 Dehavilland Aircraft Turbine
US2430398A (en) * 1942-09-03 1947-11-04 Armstrong Siddeley Motors Ltd Jet-propulsion internal-combustion turbine plant
US2435990A (en) * 1945-08-17 1948-02-17 Westinghouse Electric Corp Gas turbine lubricating oil cooling and air inlet deicing system

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2700935A (en) * 1948-04-27 1955-02-01 Bendix Aviat Corp Rocket fuel pump and the like
US2922278A (en) * 1948-11-30 1960-01-26 Szydlowski Joseph Coaxial combustion products generator and turbine
US2788951A (en) * 1951-02-15 1957-04-16 Power Jets Res & Dev Ltd Cooling of turbine rotors
US2859935A (en) * 1951-02-15 1958-11-11 Power Jets Res & Dev Ltd Cooling of turbines
US2842306A (en) * 1952-04-30 1958-07-08 Alfred Buchi Turbine driven multi-stage blower or pump
US2839005A (en) * 1953-10-14 1958-06-17 Herbert E Means Turbine driven pump
US2929207A (en) * 1955-08-08 1960-03-22 Adolphe C Peterson Axial flow gas turbine
US2931563A (en) * 1955-09-19 1960-04-05 Eggleton Frederick Construction of axial flow compressors
US3023577A (en) * 1955-10-24 1962-03-06 Williams Res Corp Gas turbine with heat exchanger
US2937495A (en) * 1956-02-27 1960-05-24 Power Jets Res & Dev Ltd Gas turbine plant
US2922618A (en) * 1956-03-06 1960-01-26 Gen Electric Turbo-machine rotor
US2990108A (en) * 1957-03-04 1961-06-27 Curtiss Wright Corp Compressor with annular discharge diffuser
US2927724A (en) * 1957-10-02 1960-03-08 Avro Aircraft Ltd Floating blade shrouds
US3037352A (en) * 1958-09-08 1962-06-05 Vladimir H Pavlecka Bypass jet engines using centripetal flow compressors and centrifugal flow turbines
US3194011A (en) * 1962-04-23 1965-07-13 Paul W Chaney Aircraft with non-combustion air reaction engine
US3259195A (en) * 1962-04-23 1966-07-05 Paul W Chaney Aircraft with non-combustion, air reaction engine
US3157991A (en) * 1963-04-16 1964-11-24 Kemenczky Establishment Flow regulating device for jet propulsion engine
US3302866A (en) * 1965-03-16 1967-02-07 Polytechnic Inst Brooklyn High velocity fluid accelerator
US3897986A (en) * 1972-12-08 1975-08-05 Rolls Royce 1971 Ltd Bearings
FR2506839A1 (fr) * 1981-05-27 1982-12-03 Onera (Off Nat Aerospatiale) Turboreacteur contra-rotatif simplifie
US6102655A (en) * 1997-09-19 2000-08-15 Asea Brown Boveri Ag Shroud band for an axial-flow turbine
WO2005021975A1 (de) * 2003-08-21 2005-03-10 Anton Niederbrunner Laufradanordnung einer strömungsmaschine
CN113153537A (zh) * 2021-03-19 2021-07-23 哈尔滨工业大学 一种应用于高超声速飞机的三轮冷却-制冷循环冷却系统
CN113153537B (zh) * 2021-03-19 2022-05-17 哈尔滨工业大学 一种应用于高超声速飞机的三轮冷却-制冷循环冷却系统

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