WO2017060581A1 - Systeme de suspension de deux modules d'un ensemble propulsif - Google Patents
Systeme de suspension de deux modules d'un ensemble propulsif Download PDFInfo
- Publication number
- WO2017060581A1 WO2017060581A1 PCT/FR2016/052387 FR2016052387W WO2017060581A1 WO 2017060581 A1 WO2017060581 A1 WO 2017060581A1 FR 2016052387 W FR2016052387 W FR 2016052387W WO 2017060581 A1 WO2017060581 A1 WO 2017060581A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- bar
- rudder
- axis
- pylon
- modules
- Prior art date
Links
- 239000000725 suspension Substances 0.000 claims description 11
- 238000011084 recovery Methods 0.000 claims description 7
- 239000007789 gas Substances 0.000 description 11
- 230000005484 gravity Effects 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 3
- 210000005069 ears Anatomy 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
-
- 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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
- B64D27/404—Suspension arrangements specially adapted for supporting vertical loads
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
- B64D27/406—Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links
Definitions
- the present invention relates to a suspension system for two modules, such as two fan modules, of a propulsion unit, in particular an aircraft.
- the state of the art includes in particular the documents EP-A2-1 916 406, US-A1-2015/274306 and US-A1-2005/067528.
- the applicant has undertaken work on an overall propulsion architecture for at least two distributed blowers. These objectives are to seek an optimization of the propulsive efficiency thanks to a high dilution rate, while maintaining an acceptable ground clearance and reduced blowers.
- a gas generator 12 typically comprises one or more compressors supplying air to a combustion chamber.
- the gases from the chamber drive one or more turbines connected to the compressors and here a free turbine 14.
- the latter is secured to a power shaft 16 coaxial with the shaft of the gas generator 12.
- This power shaft 16 drives by by means of suitable bevel gears, two intermediate radial shafts 18 and 18 'arranged transversely, in particular at right angles to the axis of the gas generator.
- the intermediate radial shafts each drive a fan shaft 20, 20 'offset and generally parallel to the axis of the gas generator.
- the power transmission is effected by means of first gears 22 and 22 'with bevel gears between the shaft 16 and the radial shafts 18 and 18' and second gears 24 and 24 'with bevel gears between the radial shafts 18, 18 and the blower shafts 20 and 20 '.
- the present invention provides a solution as needed above, which is simple, effective and economical.
- the invention proposes a suspension system of two modules of a propulsion unit, such as two fan modules, comprising a pylon, a spreader part of which is articulated on said pylon and opposite ends are articulated on connecting rods, characterized in that it further comprises a torque recovery bar, said bar having an elongated shape and being pivotally mounted on said pylon about an axis substantially parallel to an axis of elongation of said bar, opposite ends of said bar being fixed to said lifter, on either side of said part of the latter.
- the torque recovery bar makes it possible to limit the relative displacements between the modules, to simplify the integration of the propulsion unit (reduction of the size of the joints between the nacelles of the modules and between the nacelles and the pylon, reduction of the gears. installation and the master torque of the nacelles, etc.), and to limit the stresses on the nacelles (gain of potential mase).
- the system according to the invention can be used to suspend two fan modules of a propulsion unit or other types of modules, such as two engines or gas generators, of a propulsion unit.
- the system according to the invention may comprise one or more of the following features, taken separately from each other or in combination with each other: said lifter is hinged by rotary connections to said pylon and to said connecting rods,
- said axis of rotation of the bar is substantially coincident with the axis of elongation of the latter
- said ends of the bar are fixed to said rudder near said ends of the rudder
- said lifter extends substantially parallel to the axis of elongation of said bar, or has an elongated shape whose axis of elongation is substantially parallel to the axis of elongation of said bar,
- said part of the rudder is a median part or situated halfway between said rudder ends
- said part of the spreader bar is a part situated at a distance D1 from one of the ends of the spreader bar and at a distance D2 from the other end of the spreader bar, D1 being different from D2,
- said lifter comprises two support arms of said bar and having mounting holes for said bar,
- a distance L1 between said ends of the spreader is greater than a distance L2 between said ends of the bar, which is itself greater than a distance L3 between said arms of the spreader, the distances being measured along said axis of elongation of bar,
- the present invention also relates to a propulsion assembly, comprising a gas generator and at least two fan modules, characterized in that it is equipped with a system as described above, said rods being articulated respectively on said modules of blower.
- FIGS. 2 and 3 are very schematic views of fan module suspension systems of a propulsion unit
- FIG. 4 is a very schematic view of a suspension system according to the invention.
- FIGS. 5 to 8 are very schematic views similar to that of Figure 4 and illustrating the principle of operation of the system;
- FIG. 9 is a very schematic side view of the system and illustrating the mode of operation of FIG. 8.
- FIG. 4 represents a nonlimiting embodiment of the invention which concerns a system 32 for suspending two modules of a propulsion unit which comprises at least one gas generator and at least one fan.
- the suspension system 32 can be used to suspend these two modules to an aircraft.
- the system 32 essentially comprises a pylon 28, a rudder 30, rods 34, 36 thrust recovery, and a bar 40 of torque recovery.
- the tower 28 has an elongated shape and one of its longitudinal ends is articulated here on a portion 30 'of the spreader 30, which is either a median portion of the spreader or another part of the spreader as is the case in the example shown .
- This part 30 takes up the thrust forces of the two fan modules.
- the rudder 30 also has an elongate shape with an axis of elongation denoted A. Each of its longitudinal ends is articulated on one end of at least one connecting rod 34, 36, whose end opposite is intended to be articulated on one of the fan modules.
- the portion 30 'of the crossbar 30 is located at a distance D1 from the end of the crossbar 30 connected to the connecting rod 34, and at a distance D2 from the opposite end of the crossbar 30 connected to the connecting rod 36.
- D1 is greater than D2.
- the articulation means 38 of the pylon 28 to the rudder 30 and the rudder to the rods 34, 36 are preferably of the ball-and-socket type.
- the torque recovery bar 40 has an elongated shape whose elongation axis is denoted B and is substantially parallel to the axis A.
- the bar 40 is fixed rigidly to the spreader 30 and is mounted by a pivotal connection on the pylon 28.
- the bar 40 extends close to the crossbar 30 and here has a length L2 less than that L1 of the crossbar 30.
- the longitudinal ends 42 of the bar 40 are fixed on the crossbar 30 on either side of the portion 30 ', and in the vicinity of the ends of the crossbar 30 in the example shown.
- the rigid connection between the crossbar 30 and the bar 40 is made by means of a male-female connection.
- each longitudinal end 42 of the bar 40 has a section H or U-shaped whose two branches enclose the body of the rudder 30, here of rectangular section.
- the rudder 30 could have a H-shaped section body or U with two branches engaging a lug provided at the longitudinal end 42.
- the male-female connection is of the support-plane type.
- the pylon 28 comprises two arms 44 for supporting and mounting the bar 40.
- Each arm 44 comprises an orifice 46 for passage and guiding in rotation about the axis B of the bar 40.
- each arm 44 could comprise a tubular portion 48 defining an inner cylindrical surface for guiding the corresponding arm, as can be seen in the more specific example of FIGS. 10 and 11.
- the pylon 28 supports the gas generator via the inlet casing and the exhaust casing of the latter to the means of suspensions 31 disposed upstream and downstream of the pylon 28.
- the suspensions 31 comprise sets of rods arranged generally and respectively in planes transverse to the longitudinal direction of the pylon 28.
- each connecting rod 34 is connected to
- each yoke 50 comprises two ears between which extends the corresponding end of the rudder 30.
- the ears of each yoke 50 for example an axis which passes through a bore of a ball joint housed in a spherical housing of the corresponding end of the rudder.
- the same type of swivel connection can be provided between the pylon 28 and the portion 30 'of the spreader 30.
- the pylon 28 may thus comprise a yoke in which the portion 30' is inserted and mounted by a swiveling connection.
- Each link 34, 36 articulated to a fan module can be shifted (non-parallel) with respect to the axis of the gas generator.
- the offset angle can be between 5 and 15 °.
- P1 .D1 P2.D2
- Figure 6 illustrates the case where a disturbance ⁇ occurs.
- a torque C1 is applied on the rudder 30 which rotates about the pivot point (of the rotulante linkage of the rudder 30 to the pylon 28) of an angle a on the pylon.
- the bar 40 makes it possible to limit the displacements by applying a torque C2 which opposes the displacements by torsion of the bar 40.
- the magnitudes ⁇ . ⁇ and ⁇ . ⁇ represent the forces induced by the reaction of the bar 40 (resistive torque C2 equal to the induced torque C1).
- the bar 40 of torque recovery is made of high alloy steel so as to collect the forces.
- Another material further comprising temperature resistance properties can of course be used for producing the bar 40.
- a propulsion unit with different thrust fan modules can thus be suspended without technical difficulty to a structural element of the aircraft.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1805440.3A GB2557161B (en) | 2015-10-05 | 2016-09-21 | Suspension system for two modules of a propulsion unit |
US15/764,867 US10287025B2 (en) | 2015-10-05 | 2016-09-21 | System for suspending two modules of a propulsion unit |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1559451A FR3041996B1 (fr) | 2015-10-05 | 2015-10-05 | Systeme de suspension de deux modules d'un ensemble propulsif |
FR1559451 | 2015-10-05 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2017060581A1 true WO2017060581A1 (fr) | 2017-04-13 |
Family
ID=54366470
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2016/052387 WO2017060581A1 (fr) | 2015-10-05 | 2016-09-21 | Systeme de suspension de deux modules d'un ensemble propulsif |
Country Status (4)
Country | Link |
---|---|
US (1) | US10287025B2 (fr) |
FR (1) | FR3041996B1 (fr) |
GB (1) | GB2557161B (fr) |
WO (1) | WO2017060581A1 (fr) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3041996B1 (fr) * | 2015-10-05 | 2017-10-27 | Snecma | Systeme de suspension de deux modules d'un ensemble propulsif |
US10464684B2 (en) * | 2016-02-01 | 2019-11-05 | Bell Textron Inc. | Tapered sockets for aircraft engine mount assemblies |
US10384790B2 (en) * | 2016-02-01 | 2019-08-20 | Bell Textron Inc. | Engine mount assemblies for aircraft |
US11008884B2 (en) * | 2018-08-10 | 2021-05-18 | Rolls-Royce North American Technologies, Inc. | Gensets and methods of producing gensets from an engine and generator for hybrid electric propulsion |
FR3093504A1 (fr) * | 2019-03-05 | 2020-09-11 | Airbus Operations (S.A.S.) | Dispositif de liaison reliant un moteur d’aéronef et une structure primaire d’un mât d’aéronef comprenant un palonnier et un système de limitation du débattement hors plan du palonnier, aéronef comprenant un tel dispositif de liaison |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050067528A1 (en) * | 2003-06-30 | 2005-03-31 | Snecma Moteurs | Aircraft engine rear mount with thrust links and boomerang-shaped lever |
EP1916406A2 (fr) * | 2006-10-25 | 2008-04-30 | United Technologies Corporation | Système de propulsion d'avion |
US20150274306A1 (en) * | 2014-03-27 | 2015-10-01 | United Technologies Corporation | Hybrid drive for gas turbine engine |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4717094A (en) * | 1986-05-19 | 1988-01-05 | The Boeing Company | Aircraft engine mount system with vibration isolators |
FR2738034B1 (fr) * | 1995-08-23 | 1997-09-19 | Snecma | Dispositif de suspension d'un turbopropulseur |
FR2795386B1 (fr) * | 1999-06-22 | 2001-11-09 | Eurocopter France | Dispositif de suspension antivibratoire avec ressorts en torsion entre batteurs et structure, pour helicoptere |
US6330995B1 (en) * | 2000-02-29 | 2001-12-18 | General Electric Company | Aircraft engine mount |
US6296203B1 (en) * | 2000-05-24 | 2001-10-02 | General Electric Company | Snubber thrust mount |
FR2917713B1 (fr) * | 2007-06-21 | 2009-09-25 | Airbus France Sas | Dispositif d'accrochage de moteur d'aeronef et aeronef comportant au moins un tel dispositif. |
FR2918644B1 (fr) * | 2007-07-09 | 2009-10-23 | Airbus France Sas | Mat d'accrochage de moteur pour aeronef disposant d'un palonnier articule en quatre points. |
US8348191B2 (en) * | 2010-07-14 | 2013-01-08 | Spirit Aerosystems, Inc. | Fail-safe aircraft engine mounting apparatus |
FR2964364B1 (fr) * | 2010-09-03 | 2012-09-28 | Airbus Operations Sas | Mat d'accrochage de turboreacteur pour aeronef comprenant des attaches voilure avant alignees |
FR2969578B1 (fr) * | 2010-12-27 | 2013-02-08 | Snecma | Dispositif de suspension d'un turboreacteur |
FR3014840B1 (fr) * | 2013-12-17 | 2017-10-13 | Airbus Operations Sas | Ensemble pour aeronef comprenant un corps d'attache moteur equipe d'au moins une ferrure de support de manille penetrant dans le caisson du mat d'accrochage |
US9738391B2 (en) * | 2014-03-10 | 2017-08-22 | United Technologies Corporation | Engine installation system |
FR3041996B1 (fr) * | 2015-10-05 | 2017-10-27 | Snecma | Systeme de suspension de deux modules d'un ensemble propulsif |
-
2015
- 2015-10-05 FR FR1559451A patent/FR3041996B1/fr active Active
-
2016
- 2016-09-21 GB GB1805440.3A patent/GB2557161B/en active Active
- 2016-09-21 WO PCT/FR2016/052387 patent/WO2017060581A1/fr active Application Filing
- 2016-09-21 US US15/764,867 patent/US10287025B2/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050067528A1 (en) * | 2003-06-30 | 2005-03-31 | Snecma Moteurs | Aircraft engine rear mount with thrust links and boomerang-shaped lever |
EP1916406A2 (fr) * | 2006-10-25 | 2008-04-30 | United Technologies Corporation | Système de propulsion d'avion |
US20150274306A1 (en) * | 2014-03-27 | 2015-10-01 | United Technologies Corporation | Hybrid drive for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
US10287025B2 (en) | 2019-05-14 |
FR3041996A1 (fr) | 2017-04-07 |
GB2557161A (en) | 2018-06-13 |
US20180281980A1 (en) | 2018-10-04 |
FR3041996B1 (fr) | 2017-10-27 |
GB201805440D0 (en) | 2018-05-16 |
GB2557161B (en) | 2020-11-11 |
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