WO2008132315A2 - Joint tournant - Google Patents
Joint tournant Download PDFInfo
- Publication number
- WO2008132315A2 WO2008132315A2 PCT/FR2008/000295 FR2008000295W WO2008132315A2 WO 2008132315 A2 WO2008132315 A2 WO 2008132315A2 FR 2008000295 W FR2008000295 W FR 2008000295W WO 2008132315 A2 WO2008132315 A2 WO 2008132315A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rotary joint
- joint according
- gas
- pressure
- zone
- Prior art date
Links
Classifications
-
- 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
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L27/00—Adjustable joints, Joints allowing movement
- F16L27/08—Adjustable joints, Joints allowing movement allowing adjustment or movement only about the axis of one pipe
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
- B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
Definitions
- the invention relates to a rotary joint, a rotor and a propeller driven by the ejection of gas under pressure on a blade of the propeller comprising such a seal, and a turbine or a compressor also comprising such a seal.
- a helicopter is known from document FR 996 034. This comprises a rotor equipped with a propeller composed of several blades. The helicopter comprises means for generating pressurized gas and gas ejection heads disposed at the ends of the blades. The ejection of pressurized gases rotates the blades and thus allows the lift and movement of the apparatus.
- the pressurized gases must thus be conveyed from the gas generating means to the end of the blades driven in rotation via a gas conveying conduit.
- a rotating joint to ensure continuity between the movable part and the fixed part of the pipe.
- the rotating joints generally comprise first and second parts movable relative to each other about an axis of rotation.
- the invention aims to solve this technical problem by proposing a rotary joint allowing leaktightness or maintenance of controlled flow leakage at high operating pressures.
- the invention relates to a rotary joint of the aforementioned type, intended to separate a first zone of high pressure and a second zone of low pressure characterized in that the first and second parts each comprise an interface zone having a plurality of elements projecting and recessed complementary shapes, the elements protruding and recessed from one of the parts interlocking with the elements projecting and withdrawing from the other part so as to form increasing volume decompression chambers from the zone of high pressure towards the zone of low pressure, the interface zones being situated at a distance from one another; on the other without friction between them.
- the seal separates two zones corresponding to two distinct media of which at least one comprises a gas.
- One of the two media has a higher pressure than the second medium.
- the decompression chambers have increasing volume from the upper pressure medium to the lower pressure medium.
- the gases under high pressure tend to escape into the space delimited by the two interface zones of the moving parts.
- the elements recessed and projecting from each of the two interface zones form decompression chambers of increasing volume to create singular pressure losses depending on the selected profiles.
- the seal comprises at least one intermediate chamber located between two decompression chambers, whose volume is both greater than the preceding decompression chamber and the next decompression chamber.
- At least one of the two parts of the seal comprises gas suction means opening into the space defined by the two interface areas.
- At least one of the two parts of the seal comprises pressurized gas injection means opening into the space defined by the two interface areas.
- the injection of pressurized gas makes it possible to achieve a counter-pressure which further limits the leakage of gas under pressure.
- the gas injection means are adjustable.
- the injection means are disposed at the periphery of the corresponding interface zone.
- This feature makes it possible to reduce the escape of gases outside the rotary joint while creating an extended volume of gas under pressure between the two moving parts.
- the injection means open into a groove in the wall of the interface zone and extending circumferentially about the axis of rotation.
- This arrangement makes it possible to distribute the pressure created by the nozzle on the circumference of the interface zone.
- the gas injection means comprise deflectors disposed on a movable part of the seal and intended to compress the gas by a dynamic effect.
- the gas injection means comprise at least one injection nozzle.
- the projecting and recessed elements are formed by annular fins delimiting between them complementary annular grooves, the fins of one of the moving parts interlocking in the grooves of the other moving part and vice versa to delimit the decompression chambers.
- the fins have an edge forming with the bottom of the groove located opposite a progressive narrowing.
- the walls of the decompression chambers comprise roughness.
- the roughnesses comprise striations oriented toward the bottom of the decompression chamber.
- the interface areas extend concentrically to the axis of rotation and transversely to this same axis.
- the interface areas extend parallel to the direction of the axis of rotation.
- the first and second portions respectively comprise a first and a second portion of pipe, arranged along the axis of rotation of the moving parts and in the extension of one another, so as to form a pipe continuous sealed to ensure the delivery of a gas under pressure.
- the injection nozzle or nozzles are connected to one of the pipe portions.
- the pressure of the gases flowing in the pipe is caused to vary.
- insufficient or too great pressure at the injection nozzle disturbs the operation of the rotary joint.
- the connection thus created between the injection nozzle and the gas delivery pipe makes it possible to adjust the injection flow of the nozzle as well as possible without requiring special servocontrol.
- the pressure of the gases injected by the injection means is less than 10% of the pressure of the gases flowing in the pipe portions.
- the first part of the seal is secured to the wall of an enclosure delimiting a first zone of high internal pressure and a second external zone of lower pressure, and the second part is integral with a movable shaft. crossing the wall of the enclosure.
- the invention also relates to a rotor for a gas engine comprising a rotary joint as described above.
- the invention also relates to an apparatus with propellers driven by the ejection of gas under pressure on a blade of the propeller, in particular a helicopter comprising a rotor as described above.
- the payload transportable by the apparatus is increased because the power of the engine is increased.
- the invention further relates to a turbine or a compressor comprising a rotary joint as described above. In any case, the invention will be better understood from the description which follows, with reference to the attached schematic drawing showing, by way of non-limiting example, several embodiments of this rotary joint.
- Figure 1 is a schematic representation of a helicopter equipped with a rotary joint according to the invention
- Figure 2 is a longitudinal sectional view of a rotary joint
- Figure 3 is an enlarged partial view of the section shown in Figure 2.
- Figure 4 is a schematic view of the profile of a fin, in section along a plane comprising the axis of rotation of the seal.
- Figure 5 is a side view of a second seal according to the invention.
- Figure 6 is a sectional view along VI-VI of Figure 5.
- Figure 7 is an enlarged perspective view of the seal of Figure 5.
- Figure 8 is a side view of a third seal according to the invention.
- Figure 9 is a sectional view along IX-IX of Figure 8.
- Figure 10 is a schematic sectional view of a gas turbine comprising joints according to a fourth and fifth embodiment of the invention, in partial section above the axis of rotation of the turbine shaft.
- Figure 11 is a detail view of the seal equipping the turbine of Figure 10 according to the fourth embodiment.
- Figure 12 is a detail view of the seal equipping the turbine of Figure 10 according to the fifth embodiment.
- Figure 13 is a representation of the pressure in a joint according to the fourth embodiment as a function of the position in this joint.
- Figure 14 is a schematic detail view of the seal of Figure 11.
- FIG. 1 shows a helicopter 1 according to the invention, comprising a fuselage having a cabin 2 inside which are disposed turbine-type pressurized gas generating means 3.
- the pressurized gases are fed into a gas conveying pipe 4.
- the helicopter 1 further comprises a rotor 5, rotatably mounted on the fuselage via a rotary joint 6 comprising a fixed part 7 and a movable part 8 and through which the continuity of the pipe
- the rotor is equipped with blades 9 also comprising channels or conduits 10 for conveying the gases connected to the rotary joint 6, intended to bring the gases to the corresponding ends of the blades 9. These ends are equipped with ejection heads 11 of pressurized gases which, because of the torque exerted on the rotor 5, the blade drive 9.
- This type of helicopter has the advantage of not requiring a tail rotor, usually necessary to compensate for the torque exerted by a conventional drive blades. The costs of manufacturing and maintaining this type of helicopter are therefore reduced to a very large extent.
- the rotary joint 6 comprises a first fixed portion 7 and a second portion 8, rotatable relative to the fixed portion 7 about an axis of rotation A.
- the first and second parts 7, 8 respectively comprise a first 12 and a second 13 pipe portions, arranged along the axis of rotation A of the fixed and movable parts 7, 8, and in the extension of one another, so as to form a sealed continuous line for conveying a gas under pressure.
- the fixed part 7 comprises a tubular zone 14 having an end 15 disposed upstream with respect to the direction of the gas flow B, connected to the pipe 4, and a downstream end 16 facing towards the blades 9.
- the tubular zone 14 comprises an outer ring 17 serving to support a plate 18 mounted around the tubular zone 14 and fixed to the ring 17 by means of screws 19.
- a cover 20 is furthermore fixed to the fixed plate 18, on the outskirts of it.
- the cover 20 defines with the fixed plate 18 a volume intended to accommodate the movable portion 8 and perforated at the axis of rotation A, as shown in Figure 2.
- the movable portion 8 comprises a first tubular zone 21, disposed in downstream of the tubular zone 14 of the fixed part 7.
- the first tubular zone 21 has an upstream end, turned towards the fixed part and a second downstream end, turned towards the blades.
- the movable portion 8 is coupled to the blades of the helicopter 9, the latter forming or having conduits or channels for conveying the gases 10, connected to the second pipe portion 13. More specifically, the first tubular zone 21 is connected to the channels or ducts 10 of the blades 9 at its downstream end and comes, at its upstream end, facing the tubular zone 14 of the fixed part 7 so as to form a continuous flow of gas, as previously seen.
- the movable portion 8 further comprises a second tubular zone 22 of larger diameter than the first 21, forming a skirt extending from the upstream end of the first tubular zone 21 and coming to cover the downstream end 16 of the tubular zone 14 of the fixed part 7.
- the movable part 8 further comprises a plate 23 fixed to the second tubular zone 22, mounted around the tubular zone 14 of the fixed part 7 and facing the fixed plate 18.
- the movable plate 23 as well as part of the second tubular zone 22 are arranged inside the volume defined by the cover 20, the day 24 formed therein allowing the passage of the second tubular zone 22.
- ball bearings 25 are disposed between the outer wall of the tubular zone.
- a thrust bearing 28 is furthermore disposed between the cover 20 and the movable plate 23.
- the interface zones have a plurality of coaxial annular fins 29 delimiting between them complementary annular grooves, the fins 29 of one of the fixed or moving parts interlocking in the grooves of the other part and conversely leaving a clearance between the fins.
- a decompression chamber C which communicates with adjacent decompression chambers C at the edge of the fins 29.
- the fins 29 may have a beveled edge, so that the distance between the edge of the fin and the bottom of the groove facing decreases away from the axis of rotation A, as shown in Figure 4.
- This arrangement makes it possible to increase the pressure drop during the passage from a decompression chamber C to the adjacent decompression chamber C.
- the interface areas extend concentrically to the axis of rotation A and perpendicular to the same axis of rotation A and thus form baffles or labyrinth seal 30 having a proximal zone, that is to say located close to the axis of rotation, and a peripheral distal zone.
- the decompression chambers delimited by the fins and grooves have a volume increasing from the axis of rotation outwards of the interface areas, because they occupy a circumference of increasing diameter.
- the tubular zone 14 of the fixed part 7 has transverse openings 31, opening at the interface areas, more precisely in the proximal thereof.
- the fixed part 7 is furthermore equipped with pressurized gas injection nozzles 32, connected to the first pipe portion 12 and opening into the space delimited by the two interface zones 30.
- the injection nozzles 32 are furthermore equipped with pressurized gas injection nozzles 32, connected to the first pipe portion 12 and opening into the space delimited by the two interface zones 30.
- the injection nozzles open into a groove, not shown in the drawing, formed in the wall of the interface zone and extending circumferentially about the axis of rotation.
- the injection nozzles can be adjustable.
- the rotary joint is furthermore equipped with means for measuring the pressure of the gases in the conveying duct thus formed.
- the gases from the generation means 3 circulate in the conveying line 4, at a pressure that can go at least up to 15 bars and exceed this value.
- the gases then enter successively into the first 12 and the second 13 pipe portions, finally being ejected by the ejection heads 11 of the blades 9 via the pipes or channels 10 formed therein.
- a portion of the gas passes through the openings 31 and is then directed towards the space defined between the two interface zones 30.
- This baffle or labyrinth-like space creates singular pressure drops to reduce the gas leakage rate.
- the addition of a back pressure through the injection nozzles 32 further limits the gas leaks and forms a volume or cushion of gas under pressure between the two interface zones 30.
- the pressure of the gases injected by the nozzle is between 0.5 and 0.8 bar in the example.
- the gases escaping from the aforementioned volume at the peripheral zone of the plates 18, 23 are directed towards a chamber 33 delimited by the mobile plate 23, the fixed hood 20 and the thrust bearing 28. Additional openings 34 are provided in the hood 20 so as to allow the escape of the gases contained in the aforesaid chamber 33.
- these additional openings may be located at the joint plane.
- the rotary joint according to the invention although equipped with a helicopter in the embodiment described above, could also equip other types of propeller driven by the ejection of pressurized gas on a blade of the propeller.
- the rotary joint according to the invention could also be adapted to turbines or compressors, in order to solve the same technical problem, namely to ensure a satisfactory seal or controlled flow leak for large pressures.
- a second rotary joint according to the invention is intended to be used at the level of the bearing of a turbine shaft 35 partially shown in FIG. bearing is carried out at the wall 36 of an enclosure defining a zone Z1 of high internal pressure and an outer zone Z2 of lower pressure. It is desirable to ensure a satisfactory seal or controlled flow leakage between the two zones Z1, Z2 thus defined.
- the rotary joint comprises a first fixed part 37 integral with the wall 36 of the enclosure and a second movable part 38 integral with the shaft 35 of the turbine and movable in rotation with respect to the fixed part. 37.
- the first and second portions 37, 38 do not include pipe portions.
- the fixed part 37 comprises a plate 39 mounted on the wall 36 of the enclosure having a central lumen allowing the passage of the shaft 35 of the turbine.
- This plate 39 is fixed to the wall of the enclosure by means of screws 40.
- the fixed portion 37 further comprises, around the central slot of the plate 39, a housing rim 42 ball bearing, having a return 43 facing the center of the light.
- the movable portion 38 comprises a sleeve 44 mounted around the shaft 35 of the turbine and also having a bearing housing 45 ball.
- the movable portion 38 further comprises a plate 46 fixed around the sleeve 44 and facing the plate 39 of the fixed portion 37.
- the movable portion 38 finally comprises a retaining plate 47 fixed around the turbine shaft to the end of the latter, in contact with the plate 46.
- Ball bearings 48 are arranged between the housing flange 42 of the fixed part 37 and the housing 45 of the sleeve 44 of the movable part 38, via a clamping ring 49 and a spacer 50.
- the plates 39, 46 of the stationary and movable portions 37 and 37 facing each other define zones or interface surfaces facing each other and fitting into each other. the others to delimit decompression chambers of increasing volume, which communicate with adjacent decompression chambers at the edge of the fins.
- decompression chambers are all concentric with respect to the axis of rotation A of the seal.
- the fixed part of the gasket comprises at least one gas passage 52 coming from the zone of high pressure Z1 inside the chamber towards the interface zone.
- This passage 52 is formed in the wall of the enclosure, in the thickness of the plate of the fixed part, until reaching the housing of the turbine shaft with which the interface zone communicates.
- Seals 53, 54 respectively positioned between the wall 36 of the enclosure and the plate 39 of the fixed part 37 on the one hand, and between the plate 46, the mobile part 38 and the retaining plate 47 on the other hand, allow to avoid that the gas borrows a passage other than the privileged passage 52.
- the plate 46 of the movable portion 38 comprises gas injection means comprising conduits 55 disposed on the periphery of the plate communicating with the outer zone Z2, at the end of which are disposed deflectors 56.
- each deflector 56 has an ellipsoidal spoon shape whose axis is inclined at least 45% relative to the outer surface of the last decompression chamber. The presence of a deflector 56, when the shaft is rotating, generates a compression of the outside air in the conduit 55, which allows to form a back pressure in the last decompression chamber.
- the surface of the recess on the wall of the last chamber is preferably equal to that of the conduit.
- the conduits 55 are homogeneously distributed on the periphery of the edge of the plate, in communication with the last decompression chamber.
- the sum of the duct surfaces is greater than or equal to that of the clearance existing between the outer wall of the last decompression chamber and the fixed part of the rotary joint.
- the plate of the fixed part comprises a set of final conduits 57 connecting the end of the interface zone to the outer zone Z2.
- a third rotary joint according to the invention is intended, like the second embodiment, to be used to seal the bearing of a turbine shaft. 58.
- the rotary joint comprises, as in the second embodiment, a first fixed portion 59 secured to the wall of the enclosure 62 and a second movable portion 60 secured to the shaft of the turbine 58, a ball bearing 63 being interposed between the first and second parts.
- the fixed part 59 comprises a conical portion 64 mounted on the wall of the enclosure having a central lumen allowing the passage of the shaft of the turbine 58.
- the inner wall of the conical portion has fins 65 for forming the decompression chambers which extend perpendicular to the axis of rotation of the shaft 58 towards the center of the light of the conical portion.
- the size of the fins 65 increases away from the top of the cone so that the free edges of the fins are positioned on a cylinder.
- the movable portion 60 comprises a sleeve 66 fixed to the shaft and having fins 67 fixed around the shaft 58, the fins 67 extending radially relative to the shaft 58.
- the size of the fins 67 increases correspondingly at the distance between the shaft and the bottom of the grooves formed between two successive fins 65 of the conical portion 64 of the fixed part 59.
- the decompression chambers extend parallel to the axis of rotation A, the decompression chambers delimited by the fins and the grooves have a volume increasing from the zone of the top of the cone towards the base thereof, because the size of the fins 65, 67 and decompression chambers delimited by it increase.
- the fixed part 61 of the gasket comprises at least one gas passage 68 coming from the zone of high pressure Z1 inside the chamber towards the interface zone, at the apex of the conical portion 64.
- the plate of the movable part comprises, for its part, gas injection means comprising ducts 69 and baffles 70 arranged at the level of the upper part of the second sleeve, on the periphery of the shaft, similar to those described in FIG. second embodiment.
- Figure 10 shows schematically, in partial section, a turbine 80 equipped with seals 82, 83 according to the invention according to a fourth and a fifth embodiment.
- the turbine comprises a movable shaft 84 rotated about an axis A, the shaft 84 being partially housed in an enclosure 85.
- the shaft 84 comprises a set of blades 86, the blades 86 being intended to be rotated by a pressurized gas entering the chamber through a first opening 87 in the chamber and out through a second opening 88 in the chamber 85.
- Between the blades 86 are arranged the guide members of the stream 89 fixed gas relative to the enclosure 85, these flow guiding members 89 having slots 90 for limiting the turbulence of the gas flow.
- Two joints 82 according to a fourth embodiment are arranged at the connection between the enclosure 85 and the movable shaft 84.
- Mechanical connection means 92 constituted for example by bearings, make it possible to take up the mechanical forces and to ensure rotation between the shaft and the enclosure with a very low tolerance for axial movement.
- seals 83 according to a fifth embodiment of the invention are arranged between the guide members flow 89 and the shaft 84 of the turbine 80.
- a seal according to the fourth embodiment comprises two combs 93, 94 comprising alternating fins and grooves. These combs 93, 94 are interleaved and movable relative to one another so as to form chambers with increasing volume. The interface zone defined by these combs 93, 94 extending perpendicularly to the axis of rotation A.
- the seal comprises two intermediate chambers 95, positioned at substantially one-third and two-thirds of the succession of chambers of decompression, considering the radial dimension of the joint. These intermediate chambers 95 communicate upstream and downstream with the decompression chambers. These two intermediate chambers are not visible in the figure
- Figure 14 is a schematic figure in which the actual dimensions are not respected.
- the intermediate chambers 95 allow decompression of the gas in a large ratio, corresponding substantially to the ratio of volumes between the decompression chamber preceding the intermediate chamber and the latter.
- the joint comprises about 200 decompression chambers with a volume of about 7 cm3 to about 80 cm3, two intermediate chambers with a volume 10 times greater than the adjacent chambers being formed at one-third and two-thirds of the succession of chambers. decompression.
- Figure 13 shows the evolution of the pressure in the different chambers. It appears that the pressure at the second intermediate chamber is of the order of 0.2 bar. It is therefore sufficient to maintain by suction this pressure to ensure a lower pressure both the external pressure and the internal pressure.
- a first comb 93 is integral with the flow guiding members fixed on the enclosure, and the second comb 94 is integral with the shaft of the turbine.
- a seal 83 according to the fifth embodiment of the invention comprises sets of chambers 96 of increasing volume formed by two combs 97, 98 comprising fins and grooves, interleaved and movable one. compared to each other. The interface area defined by these combs 97,98 extending parallel to the axis of rotation.
- a clearance 99 is formed between the edge of the fins and the bottom of the grooves to allow longitudinal expansion of the fins.
- an intermediate chamber 100 Between two sets of chambers 96 successive increasing volume is disposed an intermediate chamber 100 whose volume is much greater than that of the chambers located adjacent to the intermediate chamber and belonging to the two sets surrounding it.
- a first comb 97 is integral with the flow guiding members fixed on the enclosure, and the second comb 98 is integral with the shaft of the turbine.
- the main applications of the invention relate, in addition to helicopters and turbines as illustrated with reference to FIGS, the engine turbines or gas turbine of combustion engines, compressed air engines, turbochargers, compressors and pumps in which must be sealed and / or leak recovery.
- the seals can be used in a centrifuge for example for isotopes of uranium or any other gaseous product, to avoid external pollution.
- the seals can be used in machine tools, for example an argon welding station comprising a rotating shaft, operating under a controlled atmosphere, in particular in clean rooms, to avoid contamination of this controlled atmosphere.
- the seals according to the invention can also be used for sealing at the level of motor shafts, for example for aircraft, boat or submarine engine shafts.
- the purpose of using a seal is to avoid the entry of liquid under high pressure into the seal.
- the seal used comprises a first part having decompression chambers of increasing volume between the inner space and an intermediate chamber, at which a gas injection is performed, then a second series of compression chamber decreasing volume between the intermediate chamber and the outside. The pressurized gas injected at the level of the intermediate chamber and compressed by the compression chambers makes it possible to maintain the liquid outside the enclosure of the submarine.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Sealing Devices (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Joints Allowing Movement (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BRPI0808698A BRPI0808698A2 (pt) | 2007-03-07 | 2008-03-06 | vedação rotativa, rotor, aeronave acionada por hélice e turbina ou compressor |
RU2009136218/11A RU2470207C2 (ru) | 2007-03-07 | 2008-03-06 | Вращающееся уплотнение |
US12/529,263 US8387910B2 (en) | 2007-03-07 | 2008-03-06 | Rotary seal |
EP08787768A EP2117927A2 (fr) | 2007-03-07 | 2008-03-06 | Joint tournant |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0701653A FR2913479A1 (fr) | 2007-03-07 | 2007-03-07 | Joint tournant et rotor correspondant pour appareil a helices entrainees par l'ejection de gaz sous pression sur une pale et de l'helice, notamment pour helicoptere. |
FR0701653 | 2007-03-07 | ||
FR0705062 | 2007-07-12 | ||
FR0705062A FR2913480B1 (fr) | 2007-03-07 | 2007-07-12 | Joint tournant |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2008132315A2 true WO2008132315A2 (fr) | 2008-11-06 |
WO2008132315A3 WO2008132315A3 (fr) | 2008-12-24 |
Family
ID=38670903
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2008/000295 WO2008132315A2 (fr) | 2007-03-07 | 2008-03-06 | Joint tournant |
Country Status (7)
Country | Link |
---|---|
US (1) | US8387910B2 (fr) |
EP (1) | EP2117927A2 (fr) |
CN (1) | CN101636318A (fr) |
BR (1) | BRPI0808698A2 (fr) |
FR (2) | FR2913479A1 (fr) |
RU (1) | RU2470207C2 (fr) |
WO (1) | WO2008132315A2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2945095A1 (fr) * | 2009-04-29 | 2010-11-05 | Xamac | Joint tournant |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8991748B1 (en) * | 2011-04-19 | 2015-03-31 | Groen Brothers Aviation, Inc. | Solid lubricated blade pitch control system for use within a compressed airstream of a reaction driven rotorcraft |
US9038940B1 (en) * | 2011-05-16 | 2015-05-26 | Groen Brothers Aviation, Inc. | Rotor configuration for reaction drive rotor system |
US9169009B1 (en) * | 2010-09-09 | 2015-10-27 | Groen Brothers Aviation, Inc. | Hub-mounted auxilliary systems for tipjets in a reaction drive rotor system |
CN102042450B (zh) * | 2010-12-06 | 2012-06-27 | 长沙中联消防机械有限公司 | 用于工程机械的中心回转接头 |
JP6002474B2 (ja) * | 2012-06-29 | 2016-10-05 | 古野電気株式会社 | レーダアンテナ装置 |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR996034A (fr) | 1945-04-12 | 1951-12-12 | Sncaso | Perfectionnements aux hélices sustentatrices à réaction et applications aux appareils à voilure tournante |
US2994495A (en) | 1959-12-10 | 1961-08-01 | Kaman Aircraft Corp | Rotor isolation and air supply mechanism for a helicopter |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB191107107A (en) | 1910-03-26 | 1911-06-01 | Ljungstroms Angturbin Ab | Improvements in Labyrinth Packings for Steam or Gas Turbines. |
FR649065A (fr) * | 1927-04-09 | 1928-12-18 | Presse-étoupe pour arbres rotatifs | |
US2115031A (en) * | 1932-03-22 | 1938-04-26 | Meininghaus Ulrich | Disk construction for radial flow machines |
US2011206A (en) * | 1934-06-22 | 1935-08-13 | Standard Oil Dev Co | Seal for rotary shafts |
DE975981C (de) * | 1952-02-20 | 1963-01-03 | Siemens Ag | Wellenabdichtung fuer Lager, insbesondere solche von elektrischen Maschinen |
FR1188483A (fr) * | 1957-01-09 | 1959-09-23 | Rotor automoteur aérien, utilisable notamment comme hélice ou moteur rotatif | |
US3259195A (en) * | 1962-04-23 | 1966-07-05 | Paul W Chaney | Aircraft with non-combustion, air reaction engine |
SU274957A1 (ru) * | 1969-02-17 | 1986-02-23 | Alekseev V I | Лабиринтное уплотнение |
SU1460431A1 (ru) * | 1984-08-28 | 1989-02-23 | Производственное объединение "Невский завод" им.В.И.Ленина | Статор центробежного компрессора |
JPH02190676A (ja) * | 1989-01-17 | 1990-07-26 | Mitsuhiro Kanao | 特に冷却機能を持つラビリンスシールシステム |
GB8907695D0 (en) * | 1989-04-05 | 1989-05-17 | Cross Mfg Co | Seals |
US5211541A (en) * | 1991-12-23 | 1993-05-18 | General Electric Company | Turbine support assembly including turbine heat shield and bolt retainer assembly |
FR2695702B1 (fr) * | 1992-09-14 | 1994-11-04 | Cga Hbs | Joint d'étanchéité à labyrinthe gazeux à jeu constant. |
US5641269A (en) * | 1995-05-30 | 1997-06-24 | Royal Aviation | Helicopter rotor seal assembly |
CA2598987C (fr) * | 2005-02-15 | 2014-05-27 | Alstom Technology Ltd | Element d'obturation pour machine a circulation de fluides |
-
2007
- 2007-03-07 FR FR0701653A patent/FR2913479A1/fr active Pending
- 2007-07-12 FR FR0705062A patent/FR2913480B1/fr not_active Expired - Fee Related
-
2008
- 2008-03-06 RU RU2009136218/11A patent/RU2470207C2/ru not_active IP Right Cessation
- 2008-03-06 CN CN200880007359A patent/CN101636318A/zh active Pending
- 2008-03-06 BR BRPI0808698A patent/BRPI0808698A2/pt not_active IP Right Cessation
- 2008-03-06 WO PCT/FR2008/000295 patent/WO2008132315A2/fr active Application Filing
- 2008-03-06 EP EP08787768A patent/EP2117927A2/fr not_active Withdrawn
- 2008-03-06 US US12/529,263 patent/US8387910B2/en not_active Expired - Fee Related
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR996034A (fr) | 1945-04-12 | 1951-12-12 | Sncaso | Perfectionnements aux hélices sustentatrices à réaction et applications aux appareils à voilure tournante |
US2994495A (en) | 1959-12-10 | 1961-08-01 | Kaman Aircraft Corp | Rotor isolation and air supply mechanism for a helicopter |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2945095A1 (fr) * | 2009-04-29 | 2010-11-05 | Xamac | Joint tournant |
Also Published As
Publication number | Publication date |
---|---|
WO2008132315A3 (fr) | 2008-12-24 |
EP2117927A2 (fr) | 2009-11-18 |
CN101636318A (zh) | 2010-01-27 |
FR2913479A1 (fr) | 2008-09-12 |
RU2009136218A (ru) | 2011-04-20 |
FR2913480B1 (fr) | 2010-10-01 |
US20100090414A1 (en) | 2010-04-15 |
US8387910B2 (en) | 2013-03-05 |
FR2913480A1 (fr) | 2008-09-12 |
RU2470207C2 (ru) | 2012-12-20 |
BRPI0808698A2 (pt) | 2016-07-19 |
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