WO2014202881A1 - Ventilation d'une nacelle de turbomachine - Google Patents
Ventilation d'une nacelle de turbomachine Download PDFInfo
- Publication number
- WO2014202881A1 WO2014202881A1 PCT/FR2014/051461 FR2014051461W WO2014202881A1 WO 2014202881 A1 WO2014202881 A1 WO 2014202881A1 FR 2014051461 W FR2014051461 W FR 2014051461W WO 2014202881 A1 WO2014202881 A1 WO 2014202881A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- nacelle
- turbomachine
- duct
- ejector
- nozzles
- Prior art date
Links
- 238000009423 ventilation Methods 0.000 title claims abstract description 13
- 238000005507 spraying Methods 0.000 claims abstract description 4
- 239000007921 spray Substances 0.000 claims description 7
- 239000012530 fluid Substances 0.000 description 9
- 238000009434 installation Methods 0.000 description 2
- 238000005461 lubrication Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/14—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid
- F04F5/16—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing elastic fluids
- F04F5/20—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing elastic fluids for evacuating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
- F04F5/46—Arrangements of nozzles
- F04F5/463—Arrangements of nozzles with provisions for mixing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
- F04F5/46—Arrangements of nozzles
- F04F5/466—Arrangements of nozzles with a plurality of nozzles arranged in parallel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/324—Application in turbines in gas turbines to drive unshrouded, low solidity propeller
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/325—Application in turbines in gas turbines to drive unshrouded, high solidity propeller
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/601—Fluid transfer using an ejector or a jet pump
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/605—Venting into the ambient atmosphere or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/608—Aeration, ventilation, dehumidification or moisture removal of closed spaces
Definitions
- the present invention relates to a turbomachine nacelle comprising ventilation means and a turbomachine comprising such a nacelle.
- turbomachine nacelle It is important that the thermal environment of a turbomachine nacelle is controlled so that equipment housed in the nacelle are not subjected to too high temperatures, which could reduce their service life.
- Several sources of heat in the turbomachine can indeed increase the surrounding temperature in the nacelle.
- the compressed air supplied by the upstream propeller makes it possible to ventilate the external surface of the nacelle, even when the mach of the aircraft equipped with this turboprop is very low or even zero (for example when the aircraft is on the ground).
- the nacelle of this turboprop engine may further be equipped with a scoop placed downstream of the propeller and intended to collect compressed air and to route it inside the nacelle for ventilation.
- the propellers may be located downstream of the engine.
- the nacelle of this turboprop engine can also be equipped with a scoop of the aforementioned type, to ensure recovery of the dynamic pressure in flight.
- the pressure difference between the scoop and the downstream of the nacelle is zero and the basket is not ventilated. It is therefore necessary to find a solution for ventilating a nacelle of this type of turbomachine, for a low mach or no mach.
- the present invention is intended to provide a simple, effective and economical solution to this problem which is particularly suitable, but not exclusively, for a turbomachine of the open rotor type.
- the invention proposes a jet-type jet ejector for a turbomachine, comprising a passage duct for a secondary flow of ventilation air, a first end of which forms an air inlet and a second end forms an air outlet.
- a jet-type jet ejector for a turbomachine comprising a passage duct for a secondary flow of ventilation air, a first end of which forms an air inlet and a second end forms an air outlet.
- two spray nozzles of a primary air flow are mounted in the duct which defines a mixer and a diffuser downstream of the nozzle, these two nozzles being parallel and adjacent to each other
- the mixer comprises two substantially flat longitudinal walls, respectively lower and upper, connected together by two side walls having in cross section a semicircular shape and the radius of curvature R2 is centered on the axis of a nozzle, the spacing of the nozzles being equal to JC 2.R2.
- the operation of a jet jet ejector is well known to those skilled in the art and is based on the principle of the Venturi effect.
- the ejector comprises a primary circuit comprising a nozzle for generating a jet of pressurized primary fluid inside a conduit of a secondary circuit.
- the conduit has an inlet and a secondary fluid outlet and defines a mixer and a diffuser downstream of the nozzle.
- the primary fluid ejected into the duct expands in the diffuser, which creates a vacuum and forces the passage of secondary fluid from the inlet to the outlet of the conduit, the secondary fluid then being mixed with the primary fluid in the conduit.
- the primary and secondary fluids are air.
- the air inlet of the duct opens into the nacelle so that air contained in the nacelle is sucked and circulates in the duct until its exit, this phenomenon causing air movements in the nacelle, which ensure its safety. ventilation, even when the aircraft equipped with a turbomachine with a nacelle according to the invention is on the ground.
- the or each ejector comprises two parallel spray nozzles and mounted next to each other.
- the efficiency of an ejector is notably related to the length of the part of the duct in which the mixing of the primary and secondary fluids (air) takes place, this length preferably being at least five times equal to the diameter or the transverse dimension of the duct. blender leads.
- the present invention makes it possible in particular to reduce the length of the ejector for a constant output section.
- the mixer of the duct here comprises two substantially flat longitudinal walls, respectively lower and upper, connected together by two side walls having a cross-section in a semicircular shape and whose radius of curvature is centered on the axis of a nozzle.
- the overall passage section defined by the conduit mixer is preferably constant and symmetrical with respect to a longitudinal median plane.
- the diameter of the mixing zone does not increase and it is possible to maintain a sufficient diameter / length ratio of the mixer.
- the double nozzle ejector is symmetrical, which also ensures the preservation of high efficiency.
- the spacing of the nozzles is advantageously equal to 7t / 2.R2, R2 being the aforementioned radius of curvature. This makes it possible to keep the same passage section with only one nozzle per ejector.
- the ejector preferably has a length of between 10 R 2 and 16 R 2.
- the longitudinal walls are substantially parallel and have substantially identical dimensions.
- the invention relates in between a ventilation system or pressurization for a turbomachine, comprising at least one ejector as described above.
- the invention also relates to a turbomachine nacelle, characterized in that it comprises at least one ejector as described above.
- the invention thus proposes to ventilate the nacelle of a turbomachine by means of one or more ejectors or jet tubes.
- Document FR-A1 -2 961 856 of the Applicant describes a jet pump for a turbomachine. It is therefore already known to use this type of ejector in a turbomachine. However, in the present invention, this ejector is used to provide ventilation of the nacelle of the turbomachine, which is not the case in the aforementioned document where the jet jet is used to degas a lubrication chamber of the engine. the turbomachine.
- the first end of the duct may form an air inlet located in the nacelle.
- the second end of the duct can lead to an outer surface of the nacelle so that the air leaving the duct is expelled to the outside of the turbomachine.
- the nacelle may comprise an annular row of ejectors regularly distributed around the longitudinal axis of the nacelle. These ejectors are for example four, eight or sixteen.
- the present invention also relates to a turbomachine, such as a turbojet or an airplane turboprop, characterized in that it comprises a nacelle of the aforementioned type, the spray nozzles being supplied with compressed air taken from a compressor of the turbomachine.
- This turbomachine can be a turbo-propeller with two propellers not keeled and counter-rotating.
- FIG. 1 is a schematic half-view in axial section of a turbomachine of the open rotor type according to the invention
- FIG. 3 is a schematic perspective view of an ejector of the nacelle according to the invention.
- FIG. 4 is a very diagrammatic view of the passage section of a mixer of an ejector conduit equipped with a single spray nozzle;
- FIG. 5 is a very schematic view of the passage section of a mixer of an ejector conduit equipped with two spray nozzles.
- turbomachine 10 being a turboprop or open rotor and having downstream two propellers 12, 14 unducted and counter-rotating.
- the turbomachine 10 comprises a motor surrounded by a nacelle 16, the engine comprising from upstream to downstream, in the direction of flow of the gases, a low-pressure compressor 18, a high-pressure compressor 20, a combustion chamber 22, a turbine high pressure 24, a low pressure turbine 26 and a power turbine 28 for driving the propellers 12, 14.
- the nacelle 16 has an annular shape and comprises an outer annular wall 30 which extends around the housings 32 of the engine and which defines therewith an annular space 34 in which are housed equipment of the turbomachine. This equipment must be ventilated during engine operation.
- the present invention proposes to ventilate the nacelle 16 by means of ejector 36 of the jet horn type mounted in the space 34 mentioned above.
- the nacelle 16 is equipped with four ejectors 36 which are regularly distributed around the longitudinal axis A of the turbomachine.
- An ejector 36 comprises a primary circuit comprising at least one nozzle 38 for spraying a primary air flow (arrow 39 - FIG. 2) inside a duct 40 of a secondary circuit.
- the duct 40 defines a passage vein of a secondary air flow (arrow 41) and comprises an air inlet 42 opening into the space 34 of the nacelle 16 and an air outlet 44 opening on the outer surface of the wall 30 for the evacuation of air to the outside of the turbomachine (arrows 45).
- the conduit 40 has an elongate shape and defines downstream of the nozzle 38 a mixer 46 and a diffuser 48, the mixer having a constant passage section while the diffuser is diverging downstream and therefore has a passage section that increases downstream.
- the primary air flow ejected by the nozzle 58 expands in the diffuser 48 which creates a vacuum and forces the passage of the secondary air flow from the inlet 42 to the outlet 44 of the duct, the air of this secondary fluid from the space 34, which induces movements and flows of air inside the nacelle 16 and ensures its ventilation.
- the pressurized air ejected by the nozzle 38 is compressed air taken from the high-pressure compressor 20 of the engine, and conveyed to the nozzle via an air line 50 schematically represented in FIG.
- the air inlet 42 of the duct 40 may open radially inwards and its air outlet 44 may open radially outwards with respect to the longitudinal axis A, as shown in FIG.
- FIG. 3 represents a preferred embodiment of an ejector 36 according to the invention, this ejector being equipped with two parallel and adjacent nozzles 38.
- the mounting of two nozzles 38 in the duct 40 reduces the axial length L and therefore the axial size of the ejector 36, this length being in particular a function of the diameter or the transverse dimension of the passage section of the mixer 46 of the conduit 40 (the length L is preferably at least five times equal to this diameter).
- FIG. 4 schematically shows the mixer 46 of an ejector duct 36 equipped with a single spraying nozzle 38.
- FIG. 5 schematically shows the mixer 46 of an ejector duct 36 equipped with two nozzles 38, as is the case in FIG. 3.
- the mixer 46 has a non-circular shape in section.
- the mixer 46 comprises two flat longitudinal walls, respectively lower 52 and upper 54, which are interconnected by curved side walls 56.
- Each of the walls 52 and 54 has a width substantially equal to this center distance I.
- the side walls 56 each have in section a semi-circular shape which extends around a nozzle 38 and of which the radius of curvature R2 is centered on this nozzle.
- the half height h of the passage section which corresponds to the distance between the axis of a nozzle 38 and one of the walls 52, 54, is equal to R2.
- the ejector of Figures 3 and 5 must be sized so that the passage area defined by its mixer 46 is equal to that of the ejector of Figure 4. It is therefore necessary that the section of passage illustrated in FIG.
- the length ratio L1 / L2 is therefore 10.R1 /10.R2 or 16.R1 / 16.R2, that is, that is 10.R2.V2 / 10.R2 or 16.R2V2 / 16.R2, or else V2, ie about 1, 4.
- the ejector of Figures 3 and 5 is 1, 4 times shorter than that of Figure 4, which represents a certain gain in terms of installation.
- the section of the primary circuit should be kept constant, if although the two nozzles 38 of the ejector of Figures 3 and 5 each have a radius 1, 4 times smaller than that of the nozzle of the ejector of Figure 3.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/898,980 US10352242B2 (en) | 2013-06-18 | 2014-06-13 | Ventilation of a turbomachine nacelle |
GB1522011.4A GB2529787B (en) | 2013-06-18 | 2014-06-13 | Ventilation of a turbomachine nacelle |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1355748 | 2013-06-18 | ||
FR1355748A FR3006998B1 (fr) | 2013-06-18 | 2013-06-18 | Ventilation d'une nacelle de turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014202881A1 true WO2014202881A1 (fr) | 2014-12-24 |
Family
ID=49111419
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2014/051461 WO2014202881A1 (fr) | 2013-06-18 | 2014-06-13 | Ventilation d'une nacelle de turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US10352242B2 (fr) |
FR (2) | FR3006998B1 (fr) |
GB (1) | GB2529787B (fr) |
WO (1) | WO2014202881A1 (fr) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102014217833A1 (de) * | 2014-09-05 | 2016-03-10 | Rolls-Royce Deutschland Ltd & Co Kg | Vorrichtung für die Ableitung eines Luftstroms aus einer freien Strömung und Flugzeugtriebwerk mit mindestens einer solchen Vorrichtung |
GB2537742A (en) * | 2015-04-17 | 2016-10-26 | Rolls Royce Plc | Convergent-divergent nozzle |
CN109060293A (zh) * | 2018-09-11 | 2018-12-21 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种提高引射式短舱进气流量的方法 |
CN110907125A (zh) * | 2018-09-17 | 2020-03-24 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种分离式半模引射式短舱动力影响试验方法 |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3042820B1 (fr) * | 2015-10-27 | 2020-05-01 | Safran Aircraft Engines | Dispositif de ventilation d'un compartiment de turbomachine |
FR3095470B1 (fr) * | 2019-04-24 | 2021-10-29 | Arianegroup Sas | Conduit pour piece de stator pour turbomachine |
CN111591452B (zh) * | 2020-04-03 | 2021-11-26 | 湖北吉利太力飞车有限公司 | 垂起飞行器的通风装置及控制方法 |
FR3123092A1 (fr) * | 2021-05-18 | 2022-11-25 | Safran Helicopter Engines | Dispositif d’entrainement d’un flux d’air principal pour une turbomachine d’aeronef |
US20230392615A1 (en) * | 2022-06-07 | 2023-12-07 | Honeywell International Inc. | Jet pump system |
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DE859983C (de) * | 1944-03-28 | 1952-12-18 | Daimler Benz Ag | Verfahren zur Daempfung des Auspuffschalls an Brennkraftmaschinen, insbesondere bei Flugmotoren, und Einrichtung zur Durchfuehrung dieses Verfahrens |
FR2343891A1 (fr) * | 1976-03-10 | 1977-10-07 | Viveros Y Paredes Ltda | Dispositif d'echappement a silencieux particulierement pour moteur a combustion interne permettant une purification des gaz d'echappement et une augmentation de puissance du moteur |
US5058704A (en) * | 1988-11-21 | 1991-10-22 | Yu Chuen Huan | Turbo jet muffler |
EP0541346A1 (fr) * | 1991-11-05 | 1993-05-12 | General Electric Company | Appareil pour le transfert de fluide |
DE19639623A1 (de) * | 1996-09-26 | 1998-04-09 | Siemens Ag | Mischung von zwei Fluidströmen an einem Verdichter |
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US20120287744A1 (en) * | 2010-01-22 | 2012-11-15 | Dow Global Technologies Llc | Mixing system comprising an extensional flow mixer |
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US4351150A (en) * | 1980-02-25 | 1982-09-28 | General Electric Company | Auxiliary air system for gas turbine engine |
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US7766280B2 (en) * | 2007-05-29 | 2010-08-03 | United Technologies Corporation | Integral suction device with acoustic panel |
DE102009010647A1 (de) * | 2009-02-26 | 2010-09-02 | Rolls-Royce Deutschland Ltd & Co Kg | Laufspalteinstellungssystem einer Fluggasturbine |
FR2946089B1 (fr) * | 2009-05-27 | 2012-05-04 | Airbus France | Dispositif de refroidissement de fluides pour propulseur a turbomachine |
JP4958967B2 (ja) * | 2009-12-15 | 2012-06-20 | 川崎重工業株式会社 | 換気構造を改良したガスタービンエンジン |
FR2955617B1 (fr) * | 2010-01-26 | 2012-10-26 | Airbus Operations Sas | Propulseur a turbomachine pour aeronef |
GB201101609D0 (en) * | 2011-01-31 | 2011-03-16 | Rolls Royce Plc | Attenuation of open rotor noise |
-
2013
- 2013-06-18 FR FR1355748A patent/FR3006998B1/fr active Active
- 2013-10-03 FR FR1359593A patent/FR3006999A1/fr active Pending
-
2014
- 2014-06-13 WO PCT/FR2014/051461 patent/WO2014202881A1/fr active Application Filing
- 2014-06-13 US US14/898,980 patent/US10352242B2/en active Active
- 2014-06-13 GB GB1522011.4A patent/GB2529787B/en active Active
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
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DE859983C (de) * | 1944-03-28 | 1952-12-18 | Daimler Benz Ag | Verfahren zur Daempfung des Auspuffschalls an Brennkraftmaschinen, insbesondere bei Flugmotoren, und Einrichtung zur Durchfuehrung dieses Verfahrens |
FR2343891A1 (fr) * | 1976-03-10 | 1977-10-07 | Viveros Y Paredes Ltda | Dispositif d'echappement a silencieux particulierement pour moteur a combustion interne permettant une purification des gaz d'echappement et une augmentation de puissance du moteur |
US5058704A (en) * | 1988-11-21 | 1991-10-22 | Yu Chuen Huan | Turbo jet muffler |
EP0541346A1 (fr) * | 1991-11-05 | 1993-05-12 | General Electric Company | Appareil pour le transfert de fluide |
DE19639623A1 (de) * | 1996-09-26 | 1998-04-09 | Siemens Ag | Mischung von zwei Fluidströmen an einem Verdichter |
US20100107616A1 (en) * | 2008-10-31 | 2010-05-06 | Cummins Filtration Ip, Inc. | Exhaust gas aspirator |
US20120287744A1 (en) * | 2010-01-22 | 2012-11-15 | Dow Global Technologies Llc | Mixing system comprising an extensional flow mixer |
US8430202B1 (en) * | 2011-12-28 | 2013-04-30 | General Electric Company | Compact high-pressure exhaust muffling devices |
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DE102014217833A1 (de) * | 2014-09-05 | 2016-03-10 | Rolls-Royce Deutschland Ltd & Co Kg | Vorrichtung für die Ableitung eines Luftstroms aus einer freien Strömung und Flugzeugtriebwerk mit mindestens einer solchen Vorrichtung |
DE102014217833B4 (de) * | 2014-09-05 | 2019-05-09 | Rolls-Royce Deutschland Ltd & Co Kg | Vorrichtung für die Ableitung eines Luftstroms aus einer freien Strömung und Flugzeugtriebwerk mit mindestens einer solchen Vorrichtung |
GB2537742A (en) * | 2015-04-17 | 2016-10-26 | Rolls Royce Plc | Convergent-divergent nozzle |
GB2537742B (en) * | 2015-04-17 | 2018-01-31 | Rolls Royce Plc | Convergent-divergent nozzle for a fire critical zone |
US10436148B2 (en) | 2015-04-17 | 2019-10-08 | Rolls-Royce Plc | Convergent-divergent nozzle |
CN109060293A (zh) * | 2018-09-11 | 2018-12-21 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种提高引射式短舱进气流量的方法 |
CN109060293B (zh) * | 2018-09-11 | 2020-07-28 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种提高引射式短舱进气流量的方法 |
CN110907125A (zh) * | 2018-09-17 | 2020-03-24 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种分离式半模引射式短舱动力影响试验方法 |
Also Published As
Publication number | Publication date |
---|---|
GB2529787A (en) | 2016-03-02 |
GB2529787B (en) | 2020-03-25 |
GB201522011D0 (en) | 2016-01-27 |
FR3006999A1 (fr) | 2014-12-19 |
US10352242B2 (en) | 2019-07-16 |
US20160138472A1 (en) | 2016-05-19 |
FR3006998B1 (fr) | 2015-06-05 |
FR3006998A1 (fr) | 2014-12-19 |
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