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US3011762A - Turbines and in particular gas turbines - Google Patents

Turbines and in particular gas turbines Download PDF

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Publication number
US3011762A
US3011762A US648605A US64860557A US3011762A US 3011762 A US3011762 A US 3011762A US 648605 A US648605 A US 648605A US 64860557 A US64860557 A US 64860557A US 3011762 A US3011762 A US 3011762A
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Prior art keywords
blades
air
turbine
blade
stator
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US648605A
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English (en)
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Pouit Robert
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Classifications

    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • 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
    • F02C3/073—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 the compressor and turbine stages being concentric
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F16J15/42—Sealings between relatively-moving surfaces by means of fluid kept in sealing position by centrifugal force
    • 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
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the object of my invention is to provide a turbine in which the movable blades are capable of resisting high temperatures and have a good efliciency.
  • the turbine according to the invention is constructed in such a way that, on the one hand, means are provided to produce, at least along a portion of the surface of at least some of the movable blades of the turbine, a laminar flow of a gaseous fluid cooler than the power gas which serves principally to the drive of the turbine and that, on the other hand, these blades are disposed in such manner as to produce an acceleration of the power gas sufficient to stabilize the laminar flow of said fluid, means being further provided to prevent leaks between the rotor and the stator of the turbine.
  • the cooling fluid is generally constituted by air.
  • the leak preventing means are necessary in consequence of the high expansion of the power gases caused by their acceleration, which expansion would produce substantial leaks if said leaks were not reduced and possibly eliminated by said means.
  • FIG. 1 is a sectional view of one movable blade of a turbine made according to my invention.
  • FIGS. 2 2 and 3 3 Show two modifications of the pneumatic means for preventing leaks between the rotor and the stator.
  • FIG. 3 shows in perspective the tips of the blades of FIG. 3
  • FIG. 4 is a longitudinal sectional view of a high pressure stage of a turbine made according to my invention.
  • FIGS. 5 and 6 show other embodiments of a turbine according to my invention with two modifications of the leak preventing means.
  • I provide, at the front 'of the main body of a movable blade 1 of the turbine, a streamlined shield 2 advantage usly made of a thin rolled refractory metal such as nickel, the rear edges of said shield 2 forming, together with the body of blade 1, calibrated air blowing slots 3. Compressed air is fed under pressure through holes 4 provided in the rim of the turbine wheel, this air penetrating between the blade body 1 and the shield 2 so as to escape tangentially to the blade through calibrated slots 3.
  • I determine the rate of flow of air through slots 3 in such manner as to obtain a laminar flow of air at the outlet of said slot over some distance along the wall of the blade body 1.
  • supplementary air blowing slots are provided in this portion of the blade, for instance by providing in the blade body 1 radial channels 5 which open into the blade surface along the whole length thereof, to form slots 6 the width and direction of the flow of air through which are adjusted by plates such as 7.
  • Plates 7 are advantageously fixed to the blades at points located upstream of slots 6, whereby, even if the flow is already turbulent upstream of slots 6 and if consequently the blade body is not very well insulated thermally from the power gases, plates 7 form a shield between the blade body and the hot gases so as to slow down the passage of heat from said gases to said blade to such a degree that the heat transmitted to the blade body at this place may be absorbed by the air circulating in channels 5.
  • the cooling surface of channels 5 may advantageously be increased by providing ribs or corrugations 8 therein.
  • the torque'to be applied to the rotor is, at least partly, obtained by the reaction of the power gases as they leave the turbine wheel, this result being obtained in the known manner which consists in giving a convergent shape to at least the leading portions of the passages through which the power gases circulate between the blades, the convergence continuing at least up to a throat approximately at 1' in the trailing area of the blades, whereby said gases undergo an acceleration and a partial expansion in said passages.
  • At least a portion of the air under pressure that is used for partly cooling the turbine blades serves to create a peripheral countercurrent flowing in a direction opposed to that of the stream of power gases in the intervals between the blades.
  • the rear portions of the blades are constituted by hollow bodies 9 made of a thin rolled refractory metallic alloy. Air pressure at low temperature is made to flow through said hollow bodies 9. This air is introduced, for instance as shown on FIG.. 2, through holes 10 provided in the rim 26. of the turbine wheels;
  • I assemble shields 2, plates 7 and hollow parts 9 on the one hand with the blade body 1 through pins 29 which lock extensions of said elements 2, 7, 9 in slots 31, and on the other hand with the rim 26'of the turbinewheel through flat parts 32 bent at right angles from said pieces 2, 7, 9 and fixed in any suitable manner, for instance by riveting, on said rim 26.
  • I may use, to constitute thebodies of said'blades,
  • non refractory materials and possibly light alloys, for instance aluminum which are particularly well adapted for casting under pressure or sintering, so as to obtain at low price rotors of low inertia capable of turning at high speed.
  • Peripheral leaks may be prevented in different ways, as shown by FIGS. 2 and 3.
  • FIGS. 2 and 2 I provide in stator 11 a toroidal chamber partly filled with a ring 12 advantageously made of graphite and constituted by several adjoining elements assembled in juxtaposition by means of screws such as 13.
  • the intervals 14 between ring 12 and the tips of blades 1 may be very small since, in case of too great an expansion of blades 1, said blades can cut their way through the graphite material without serious consequences.
  • annular space 15 which establishes a communication between the upstream and the downstream sides of blades 1.
  • the power gases passing through space 14 and which constitute the gaseous leaks are driven by the ejection of cooling air from hollow bodies 9 so as to follow a trajectory between ring 12 and the wall of the chamber provided in the stator, as indicated by the arrows.
  • ring 12 is tangent to the resultant of the velocity of the gases passing through the leak passage 14 and the velocity of ejection of air from channels 9.
  • a gaseous mixture thus formed flows around rin 12 through passages 15 and is returned to the upstream side of blades 1 where it is driven by the main current of gases into the spaces provided between the turbine blades, where it expands together with the power fluid.
  • FIGS, 3 and 3 I provide in the stator an annular recess 1'6 closed on the side of the stator by wall 17 and on the side of the rotor, between the blades 1 thereof, by partitions 18 extending between the hollow trailing portions 9 of the blades (see FIG. 3 Said chamber'l'6 is fed with air under pressure through-radial conduits 9 which distributesaid air on the one hand through spaces 14 toward the upstream side of the turbine wheel, thus pushing back the gas tending to leak through said spaces 14, on the otherhand between blades 1, toward the passages 20 existing beair and gases can pass.
  • the cooling air that is used to prevent power gases from leaking past the turbine wheel is always conveyed, together with said gas leaks, toward the upstream tween said blades and through which the main flow of side of the turbine wheel, so that it is possible to recuperare, in the form of expansion work, most of the work spent'for compressing the air that has been used both to prevent gas leaks and also to cool'down the hollow frontan d. intermediate portions "of the blades and to the .j cooling of the rear portions thereof.
  • the compressed air used for these two purposes and also to prevent gas leaks must be at a pressure higher than the total pressure (i.e. both thestatic and dynamic pressures) of the power gases so that it can acquire by expansion a velocity at least equal to the velocity of flow of the power fluid, account being taken of the fact that this air is at a temperature lower than that of the power gases.
  • the compressed air that is used may be obtained from an external source. It may also be produced by an auxiliary compressor mechanically driven by the turbine. Preferably, this air is collected'from one or several compression elements existing in the power plant for feeding the combustion chambers.
  • compressed air is collected from the last compression stage 21 through conduits 22 leading to a manifold 23 in which the hollow shaft 24 rotates. This compressed air enters the hollow inside of shaft 24 and flows out therefrom through radial channels 25 provided in arms 27 so as to enter the turbine blades 1 through orifices 10 provided in the rim 26 of the turbine blade.
  • the compressed air collected from the high pressure compressor 21 may advantageous be cooled down by cooling ribs 28, before it is reintroduced into the rotor.
  • the movable blade system is constituted, as above, by blades 1 having, at their rear parts, hollow bodies 9 through which cooling air is fed to orifices 33 provided in an annular sleeve 34 toward an annular recess 16 provided in stator 11 in a manner analogous to what is shown in FIG. 3
  • This recess 16 of suitable shape conveys the air from orifices 33 toward the upstream side of turbine blades 1.
  • a flange 35 carried by said sleeve 34 is provided with an annular groove 38 divided into two communicating adjacent portions by a flange 39 fixed to stator 11.
  • This annular groove 38 is advantageously provided with fins 471 extending in radial planes.
  • the peripheral speed of the blade system 1 is supposed to be 250 meters per second, the contn'fugal acceleration at a distance from the rotation axis equal to 0.175 111. could be that is-to say 257,000. Its value is equal to 36,500 times the acceleration of gravity. It follows that the difference of oil level in the two respective adjacent portions of groove 38 to balance the pressure of 7 kg./sq. cm.
  • the energy difference between compression and expansion of the cooling air makes it possible to cool adequately the blades of the rotor and the flange thereof. Furthermore, since any air loss due to the annular clearance between the rotor and the stator is avoided, it is possible to obtain a high degree of reaction in the convergent passages between the movable blade and to stabilize, by the increase of velocity that results therefrom, the laminar flow of the fluid in the vicinity of the wall of the blades, and also the laminar flow of the insulating air layer interposed between the wall of said blades and the power fluid.
  • the liquid level difference between the two adjoining chambers of groove 38 must be higher as the speed of rotation of the turbine blades is lower. It follows that, during the starting period, a hydraulic joint of the dimensions above mentioned would have no efliciency whatever and the liquid would be driven by the air under pressure escaping between the walls of groove 38 and those of flange 39. This is why the liquid of the hydraulic joint is introduced into said groove only when the turbine is rotating at a relatively high speed.
  • the air loss at the joint between the rotor and the stator is limited by providing, between annular space 16 and groove 38, successive expansion chambers such as 42 and 42 acting in bathe-like fashion, so as to form eddies which dissipate the kinetic energy, said eddies opposing a direct flow of the fluid.
  • the cooling air is introduced into the conduits 9 of blades 1 through an axial channel 43 provided in shaft 44, and that air penetrates into channel 43 from a chamber 45
  • I may introduced the liquid which is to constitute the hydraulic joint into the cooling air itself, by injection of the atomized liquid (this liquid being preferably water in this case) into chamber 45 through injectors 46.
  • the droplets of atomized water carried along by the compressed air which they cool down separate from said air in the first expansion chamber 42, the radius of which is smaller than that of groove 38.
  • I advantageously dispose blades such as 47 and the external bottom of said chamber 42 is connected with groove 38 through conduits 48 through which flows the liquid separated in chamber 38 which is filled with said liquid.
  • the hydraulic joints shown in FIGS. 5 and 6 may also be applied to steam turbines working on the reaction principle and where it is advantageous to eliminate steam losses by preventing leaks between the rotor blade tips and the stator.
  • the hydraulic joints are preferably fed from the condensation water which is obtained at the last low pressure stage.
  • the combustion chambers where fuel is burnt with air under pressure might be constituted by the power chambers of hot gas generators, for instance of the free piston type.
  • a gas turbine which comprises in combination, a stator and a rotor, said rotor including a turbine wheel, a multiplicity of turbine blades radially fixed to the rim of said wheel, a source of compressed air substantially at ordinary temperature, means for blowing air from said source along at least a portion of the surface of each of said blades to form a laminar flow of cooling air thereon, said blades being arranged so that the passages between them are convergent in the direction of flow of the power gases flowing between them to produce an acceleration of said power gases suflicient to stabilize said fluid laminar flow, the trailing edges of said blades being provided with radial conduits leading to the tips of said blades, means for feeding air from said source to said radial conduits, the inner wall of said stator being provided, opposite the tips of said blades, with an annular recess shaped to cause at least most of the air streams that flow out from said radial conduits at the tips of said blades to be deflected toward the upstream side of said
  • At least one streamlined shield extending around the leading edge of each of said blade bodies at a distance therefrom, said shield being made of thin rolled refractory metal, and means for blowing air under pressure into the space between said shield and said blade body, the rear edges of said shield forming, with the side fans of said blade body, slots running along the span of said blade body and through which said air escapes tangentially to said body to form a laminar flow air stream along said body.
  • a turbine according to claim 2 further including a rearward extension rigid with each of said shields, each of said blade bodies being provided with a slot located in the front portion thereof to accommodate said extension, and means fitting in said last mentioned slot for locking said extension therein.
  • a turbine according to claim 1 further including a hollow body made of a refractory metal fixed to each of said blade main bodies to form the trailing edge portions thereof, the interiors of the hollow bodies constituting said radial conduits.
  • a turbine according to claim 1 in which the downstream face of each of said blade bodies is provided with a supplementary air blowing slot and a plate fixed on said face of said blade body so as partly to close said slot.
  • a turbine according to claim 1 in which the outlets of said radial air conduits are shaped to send a portion of the air flowing through said conduits toward the spaces between the tips of said blades.
  • a turbine according to claim 1 further including, in said annular recess, an annular member the inner surface of which is close to the tips of said blades as they pass along said member, the outer face of said annular member forming, with the bottom of said annular recess, a curved passage for the flow of air from the tips of the blades in the upstream direction.
  • a ring-shaped flange rigid with the downstream ends of the tips of said blades, said flange being spaced from said stator, said ringshaped flange beingprovided with an annular groove having its opening turned inwardly toward the axis of said wheel, said stator including, rigid with the downstream end thereof, an annular extension passing around said first mentioned flange to form an annular flange, substantially located in a plane at right angles to said axis, extending into said grooves so as to form with the inner wall thereof an annular space of U-shaped section by a plane passing through said axis, and means for feeding a liquid into said space to form a hydraulic joint.
  • a turbine according to claim 10 further including, in said space, fins substantially located in planes passing through said axis.
  • a ring-shaped flange rigid with the downstream ends of the tips of said blades, said flange being spaced from said stator, said ring-shaped flange being provided with an annular groove having its opening turned inwardly toward the axis of said Wheel, said stator including, rigid with the downstream end thereof, an annular extension passing around said first mentioned flange to form an annular flange, substantially located in a plane at right angles to said axis, extending into said grooves so as to form with the inner wall thereof an annular space of U-shaped section by a plane passing through said axis, and means for feeding a liquid into said space to form a hydraulic joint, the annular space between said 'first mentioned flange and saidstator being in communication with said annular recess in the inner wall of said stator opposite the tips of said blades.
  • a turbine according to claim 14 in which the communication between said annular space and said annular recess forms at least one annular expansion chamber'with battles for the formation of eddies.
  • a turbine according tov claim 14 in which the communication between said annular space and said annular recess forms at least one annular expansion chamber with baffles for the formation of eddies, said chamber being at a distance from said axis smaller than the distance from said axis to the bottom of said U-shaped section annular space, said first mentioned flange being provided with condu'itsffor connecting said chamber with said U-shaped section annular space.
  • a turbine according to claim 16 further including, in said annular expansion chamber, fins located in planes passing through said axis.
  • a turbine according to claim 14 in which said liquid feeding means are arranged to inject water into the air streams flowing through said radial conduits.
  • a turbine according to claim 1 further including partitions extending across the spaces between the trailing edge portions of the tips of said blades.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US648605A 1956-03-28 1957-03-26 Turbines and in particular gas turbines Expired - Lifetime US3011762A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR711564 1956-03-28
FR718343 1956-07-10

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US3011762A true US3011762A (en) 1961-12-05

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US (1) US3011762A (de)
CH (1) CH368973A (de)
DE (1) DE1110469B (de)
FR (1) FR1155958A (de)
GB (1) GB825967A (de)

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3409968A (en) * 1966-10-03 1968-11-12 Borg Warner Method of making a slotted blade by extruding
US3597102A (en) * 1968-06-10 1971-08-03 English Electric Co Ltd Turbines
US3620640A (en) * 1969-03-27 1971-11-16 Aerospatiale Propeller or fan shrouds
US3885886A (en) * 1972-06-27 1975-05-27 Mtu Muenchen Gmbh Unshrouded internally cooled turbine blades
US3897169A (en) * 1973-04-19 1975-07-29 Gen Electric Leakage control structure
US4238170A (en) * 1978-06-26 1980-12-09 United Technologies Corporation Blade tip seal for an axial flow rotary machine
US4571937A (en) * 1983-03-08 1986-02-25 Mtu - Motoren-Und Turbinen-Munchen Gmbh Apparatus for controlling the flow of leakage and cooling air of a rotor of a multi-stage turbine
US5230605A (en) * 1990-09-25 1993-07-27 Mitsubishi Jukogyo Kabushiki Kaisha Axial-flow blower
US5282718A (en) * 1991-01-30 1994-02-01 United Technologies Corporation Case treatment for compressor blades
US5308225A (en) * 1991-01-30 1994-05-03 United Technologies Corporation Rotor case treatment
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US6637208B2 (en) * 1997-10-22 2003-10-28 General Electric Company Gas turbine in-line front frame strut
US20040156714A1 (en) * 2002-02-28 2004-08-12 Peter Seitz Recirculation structure for turbo chargers
EP1422383A3 (de) * 2002-11-20 2006-05-31 Mitsubishi Heavy Industries, Ltd. Kühlung einer Gasturbinenschaufel
JP2007211660A (ja) * 2006-02-08 2007-08-23 Toyota Motor Corp チップタービンファン
US20080203236A1 (en) * 2007-02-27 2008-08-28 Siemens Power Generation, Inc. CMC airfoil with thin trailing edge
US20110109092A1 (en) * 2009-05-23 2011-05-12 Abel Echemendia Windmill electric generator for hydroelectric power system
EP2151582A3 (de) * 2008-08-08 2014-04-16 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine
US20140356144A1 (en) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Assembly for a fluid flow machine
US9074605B2 (en) * 2009-08-31 2015-07-07 Snecma Turbine engine compressor having air injections
US10106246B2 (en) 2016-06-10 2018-10-23 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10315754B2 (en) 2016-06-10 2019-06-11 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10683077B2 (en) 2017-10-31 2020-06-16 Coflow Jet, LLC Fluid systems that include a co-flow jet
US11111025B2 (en) 2018-06-22 2021-09-07 Coflow Jet, LLC Fluid systems that prevent the formation of ice
US11248473B2 (en) * 2016-04-04 2022-02-15 Siemens Energy, Inc. Metal trailing edge for laminated CMC turbine vanes and blades
US11293293B2 (en) 2018-01-22 2022-04-05 Coflow Jet, LLC Turbomachines that include a casing treatment
US11920617B2 (en) 2019-07-23 2024-03-05 Coflow Jet, LLC Fluid systems and methods that address flow separation
US12202602B2 (en) 2020-06-17 2025-01-21 Coflow Jet, LLC Fluid systems having a variable configuration
US12352235B2 (en) 2021-03-26 2025-07-08 Coflow Jet, LLC Wind turbine blades and wind turbine systems that include a co-flow jet

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2916332A (en) * 1958-09-08 1959-12-08 Vladimir H Pavlecka Aerostatic bearings with fluid-dynamic seals
US4130373A (en) * 1976-11-15 1978-12-19 General Electric Company Erosion suppression for liquid-cooled gas turbines
JPS5477820A (en) * 1977-12-02 1979-06-21 Hitachi Ltd Method of cooling gas turbine blade
US4335885A (en) * 1980-08-19 1982-06-22 Mechanical Technology Incorporated Plural fluid magnetic/centrifugal seal
US4576547A (en) * 1983-11-03 1986-03-18 United Technologies Corporation Active clearance control
US4648241A (en) * 1983-11-03 1987-03-10 United Technologies Corporation Active clearance control
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
US4928978A (en) * 1988-04-07 1990-05-29 United Technologies Corporation Rotating shaft seal

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE313128C (de) *
GB191210179A (en) * 1911-05-04 1912-06-20 Heinrich Holzer Arrangement for Diminishing Clearance Losses in Turbines and Pumps for Liquids and Elastic Fluids.
US1255650A (en) * 1916-03-28 1918-02-05 Gen Electric Elastic-fluid turbine.
CH221408A (de) * 1941-01-23 1942-05-31 Sulzer Ag Mehrteilige gekühlte Schaufel, insbesondere für Gasturbinen.
US2378372A (en) * 1937-12-15 1945-06-12 Whittle Frank Turbine and compressor
US2399009A (en) * 1944-07-25 1946-04-23 Gen Electric Elastic fluid turbine
GB668434A (en) * 1948-11-06 1952-03-19 Helsingor Skibsvaerft Og Maski Improvements in and relating to internal combustion turbines
US2598176A (en) * 1947-03-11 1952-05-27 Power Jets Res & Dev Ltd Sealing device
GB679530A (en) * 1947-05-23 1952-09-17 Edward Archibald Stalker Improvements in gas turbine blades
US2622843A (en) * 1947-12-17 1952-12-23 Packard Motor Car Co Turbine construction for turbojet engines
US2649278A (en) * 1948-07-15 1953-08-18 Edward A Stalker Rotor construction for fluid machines
US2685429A (en) * 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR963823A (de) * 1950-07-21
DE343982C (de) * 1921-11-08 Christian Lorenzen Gasturbine mit durch die Turbinenschaufeln hindurchgefuehrter Verbrennungsluft
DE386276C (de) * 1921-04-02 1923-12-18 Conrad Baerwolff Dipl Ing Lauf- und Leitzeugkuehlung fuer Verbrennungsturbinen
GB340421A (en) * 1929-01-18 1931-01-01 Vladimir Kalabek Gas turbine
DE491738C (de) * 1929-02-28 1930-02-12 Maschf Augsburg Nuernberg Ag Einrichtung zur Kuehlung der Laufschaufeln von Gasturbinen, bei welcher das Kuehlmittel unter Druck durch die hohl ausgebildeten Laufschaufeln gefuehrt wird
BE407456A (de) * 1934-01-29
DE720039C (de) * 1935-12-14 1942-04-22 Gustav Huhn Fa Dichtung, bestehend aus einem Graphit- oder Graphitkohlering mit metallischem Mantel
DE858334C (de) * 1940-09-29 1952-12-04 Versuchsanstalt Fuer Luftfahrt Einrichtung zur Kuehlung einer innengekuehlten, hohlen Laufschaufel fuer Gasturbinen
CH225231A (de) * 1940-11-16 1943-01-15 Sulzer Ag Gekühlte Hohlschaufel.
CH218976A (de) * 1940-12-24 1942-01-15 Sulzer Ag Gasturbinenschaufel mit Luftfilmkühlung.
GB563727A (en) * 1942-03-12 1944-08-28 British Thomson Houston Co Ltd Improvements in and relating to sealing arrangements for elastic fluid turbines and the like
CH242703A (de) * 1944-12-18 1946-05-31 Oerlikon Maschf Gekühlte Turbomaschine.
FR963825A (de) * 1945-10-22 1950-07-21
GB680581A (en) * 1949-05-09 1952-10-08 Hermann Oestrich Means for cooling the blades of gas turbine engines
GB742477A (en) * 1952-10-31 1955-12-30 Rolls Royce Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE313128C (de) *
GB191210179A (en) * 1911-05-04 1912-06-20 Heinrich Holzer Arrangement for Diminishing Clearance Losses in Turbines and Pumps for Liquids and Elastic Fluids.
US1255650A (en) * 1916-03-28 1918-02-05 Gen Electric Elastic-fluid turbine.
US2378372A (en) * 1937-12-15 1945-06-12 Whittle Frank Turbine and compressor
CH221408A (de) * 1941-01-23 1942-05-31 Sulzer Ag Mehrteilige gekühlte Schaufel, insbesondere für Gasturbinen.
US2399009A (en) * 1944-07-25 1946-04-23 Gen Electric Elastic fluid turbine
US2598176A (en) * 1947-03-11 1952-05-27 Power Jets Res & Dev Ltd Sealing device
GB679530A (en) * 1947-05-23 1952-09-17 Edward Archibald Stalker Improvements in gas turbine blades
US2622843A (en) * 1947-12-17 1952-12-23 Packard Motor Car Co Turbine construction for turbojet engines
US2649278A (en) * 1948-07-15 1953-08-18 Edward A Stalker Rotor construction for fluid machines
GB668434A (en) * 1948-11-06 1952-03-19 Helsingor Skibsvaerft Og Maski Improvements in and relating to internal combustion turbines
US2685429A (en) * 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3409968A (en) * 1966-10-03 1968-11-12 Borg Warner Method of making a slotted blade by extruding
US3597102A (en) * 1968-06-10 1971-08-03 English Electric Co Ltd Turbines
US3620640A (en) * 1969-03-27 1971-11-16 Aerospatiale Propeller or fan shrouds
US3885886A (en) * 1972-06-27 1975-05-27 Mtu Muenchen Gmbh Unshrouded internally cooled turbine blades
US3897169A (en) * 1973-04-19 1975-07-29 Gen Electric Leakage control structure
US4238170A (en) * 1978-06-26 1980-12-09 United Technologies Corporation Blade tip seal for an axial flow rotary machine
US4571937A (en) * 1983-03-08 1986-02-25 Mtu - Motoren-Und Turbinen-Munchen Gmbh Apparatus for controlling the flow of leakage and cooling air of a rotor of a multi-stage turbine
US5230605A (en) * 1990-09-25 1993-07-27 Mitsubishi Jukogyo Kabushiki Kaisha Axial-flow blower
US5282718A (en) * 1991-01-30 1994-02-01 United Technologies Corporation Case treatment for compressor blades
US5308225A (en) * 1991-01-30 1994-05-03 United Technologies Corporation Rotor case treatment
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US6637208B2 (en) * 1997-10-22 2003-10-28 General Electric Company Gas turbine in-line front frame strut
US20040156714A1 (en) * 2002-02-28 2004-08-12 Peter Seitz Recirculation structure for turbo chargers
US6935833B2 (en) * 2002-02-28 2005-08-30 Mtu Aero Engines Gmbh Recirculation structure for turbo chargers
CN100395432C (zh) * 2002-02-28 2008-06-18 Mtu飞机发动机有限公司 用于涡轮压缩机的循环结构
EP1422383A3 (de) * 2002-11-20 2006-05-31 Mitsubishi Heavy Industries, Ltd. Kühlung einer Gasturbinenschaufel
JP2007211660A (ja) * 2006-02-08 2007-08-23 Toyota Motor Corp チップタービンファン
US20080203236A1 (en) * 2007-02-27 2008-08-28 Siemens Power Generation, Inc. CMC airfoil with thin trailing edge
WO2008105866A3 (en) * 2007-02-27 2008-10-30 Siemens Power Generation Inc Cmc airfoil with thin trailing edge
US7887300B2 (en) 2007-02-27 2011-02-15 Siemens Energy, Inc. CMC airfoil with thin trailing edge
EP2151582A3 (de) * 2008-08-08 2014-04-16 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine
US20110109092A1 (en) * 2009-05-23 2011-05-12 Abel Echemendia Windmill electric generator for hydroelectric power system
US7956486B2 (en) * 2009-05-23 2011-06-07 Abel Echemendia Windmill electric generator for hydroelectric power system
US9074605B2 (en) * 2009-08-31 2015-07-07 Snecma Turbine engine compressor having air injections
US20140356144A1 (en) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Assembly for a fluid flow machine
US9664204B2 (en) * 2013-05-31 2017-05-30 Rolls-Royce Deutschland Ltd & Co Kg Assembly for a fluid flow machine
US11248473B2 (en) * 2016-04-04 2022-02-15 Siemens Energy, Inc. Metal trailing edge for laminated CMC turbine vanes and blades
US11273907B2 (en) 2016-06-10 2022-03-15 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10315754B2 (en) 2016-06-10 2019-06-11 Coflow Jet, LLC Fluid systems that include a co-flow jet
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US11034430B2 (en) 2017-10-31 2021-06-15 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10683076B2 (en) 2017-10-31 2020-06-16 Coflow Jet, LLC Fluid systems that include a co-flow jet
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US11987352B2 (en) 2017-10-31 2024-05-21 Coflow Jet, LLC Fluid systems that include a co-flow jet
US11293293B2 (en) 2018-01-22 2022-04-05 Coflow Jet, LLC Turbomachines that include a casing treatment
US11111025B2 (en) 2018-06-22 2021-09-07 Coflow Jet, LLC Fluid systems that prevent the formation of ice
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CH368973A (fr) 1963-04-30
FR1155958A (fr) 1958-05-12
DE1110469B (de) 1961-07-06
GB825967A (en) 1959-12-23

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