EP2536941A2 - Glissière à articulation - Google Patents

Glissière à articulation

Info

Publication number
EP2536941A2
EP2536941A2 EP11751969A EP11751969A EP2536941A2 EP 2536941 A2 EP2536941 A2 EP 2536941A2 EP 11751969 A EP11751969 A EP 11751969A EP 11751969 A EP11751969 A EP 11751969A EP 2536941 A2 EP2536941 A2 EP 2536941A2
Authority
EP
European Patent Office
Prior art keywords
cowl member
slider track
cowl
fan nozzle
stowed position
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP11751969A
Other languages
German (de)
English (en)
Inventor
Alan Roy Stuart
John Robert Fehrmann
Melanie Zoe Cox
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2536941A2 publication Critical patent/EP2536941A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/10—Varying effective area of jet pipe or nozzle by distorting the jet pipe or nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections

Definitions

  • Embodiments disclosed herein relate generally to an articulating slider track for a cowl member to provide a variable area fan nozzle for a gas turbine engine.
  • Conventional gas turbine engines include a fan section and a core engine with the fan sec tion having a larger outer diameter than that of the core engine,
  • the fan section and the core engine are disposed sequentially about a longitudinal axis and are enclosed in a nacelle,
  • An annular path of primary airflow passes through the fan section and the core engine to generate primary thrust.
  • An annular path of duct or fan flow (bypass air), disposed radially outward of the primary airflow path, passes through the fan section and exits through a fan nozzle to generate fan thrust.
  • bypass air flows through a region defined between an outer surface of an engine core cowl and an inner surface of the nacelle.
  • the fan nozzles of certain conventional gas turbine engines have fixed geometry.
  • the fixed geometry fan nozzles must be suitable for take-off and landing conditions, as well as for cruise conditions.
  • the requirements for take-off and landing conditions are different from requirements for the cruise condition, For cruise conditions, it is desirable to have a smaller area or smaller diameter fan nozzle for increasing cruise performance and for maximizing fuel efficiency, whereas, for take-off and landing conditions, smaller diameter fan nozzles will create more noise and may cause an engine stall. Therefore, in many conventional engines, the cruise performance and fuel efficiency are often compromised to ensure safety of the gas turbine engine at take-off and landing,
  • variable area nozzles have the ability of having a smaller fan exit nozzle diameter during cruise conditions and a larger fan exit nozzle diameter during take-off and landing conditions.
  • Known existing variable area nozzles may employ complex mechanisms that require extensive maintenance, which is desirably avoided for commercial aircraft. Further, known variable area nozzle mechanisms may add significant weight to the engine, which adversely affects performance.
  • variable area nozzles have been introduced into some gas turbine engines, there remains a need for a variable area nozzle that does not require extensive maintenance, and does not add significant weight to the gas turbine engine.
  • known gas turbine engine designs include thrust reverser assemblies.
  • known cascade type thrust reverser assemblies employ an aft translatable cowl (transcowl) that engages with a stationary cowl member in a nacelle assembly.
  • the transcowl cooperates with a core engine cowl to define at least a. portion of the annular bypass duct that terminates at the exit nozzle.
  • Movement of the translatable cowl (transcowl) away from the stationary cowl member opens a passageway through which fan by-pass air may flow.
  • a cascade structure disposed in the passageway is selectively covered and uncovered by movement of the transcowl.
  • the cascade structure includes flow directing louvers to redirect bypass air outward and forward to provide reverse thrust.
  • a plurality of actuators may be utilized to effect movement of the transco wl
  • the thrust reverser assembly may mclude blocker doors that move into the bypass duct to inhibit passage of the bypass air through the exit nozzle. Alternately, some thrust reversers are known as "blocker-door-less" types in which the translatable cowl cooperates with the engine core cowl to inhibit passage of the bypass air without employing blocker doors.
  • the thrust reverser assembly may include two half-cowls, sometimes referred to as C-ducts or D-ducts that include upper (hinge) and lower (latch) beams, The transcowl(s) may be mounted on rails or slider tracks fixed to upper and lower beams.
  • the upper beam is the main hinge beam that allows the thrust reverser assembly to open for engine access and removal.
  • the lower beam provides a means for locking together the two half-cowls.
  • exemplary embodiments that provide an assembly comprising a first slider track able to support a first cowl member; a support, member; and a mechanism in supported connection with the first slider track and the support member; wherein the mechanism is operable to mount the first slider track in articulatable relationship relative to the support member.
  • Another exemplary embodiment includes an assembly comprising a first cowl member; and a fan nozzle at least partially defined by a surface of the first cowl member, wherein the fan nozzle is associated with a fan nozzle exit area; and a mechanism in operable connection with the first cowl member being operable to slightly modify a position of the first cowl member between a nominal stowed position and a modified stowed position, such, that the fan nozzle exit area is variable with the position of the first cowl member.
  • Another exemplary embodiment provides a method for varying a fan nozzle exit area.
  • the method comprises mounting a first slider track in articualtable relationship with a support member; mounting a first cowl member in supported slidable relationship with a first slider track such that a fan nozzle is at least partially defined by a surface of the first cowl member; varying an operational position of the first cowl member by articulating the first slider track without sliding the first cowl member with respect to the first slider track such that the first cowl member moves between a stowed position and a modified stowed position, wherein a first nozzle exit area is associated with the stowed position of the first cow] member and a second, different nozzle exit area is associated with the modified stowed position of the first cowl member.
  • FIG. 1 is a schematic representation of a gas turbine engine.
  • FIG. 2 is a side view of a gas turbine engine with a tratiscowl not shown for simplicity.
  • FIG. 3 is a schematic representation of a portion of a thrust rev erser assembly.
  • FIG. 4 is a schematic top view of a hinge beam and a slider track showing a plurality of 4-bar linkages.
  • FIG. 5 is a schematic side view showing a slider track and a 4-bar linkage.
  • Exemplary embodiments disclosed herein provide thrust reverse* assemblies that may be utilized to provide the desired variable area of fan exit nozzles.
  • FIG. 1 illustrates a schematic view of selected portion of an exemplary gas turbine engine 10 suspended from an engine pyl on 12 of an associated aircraft.
  • the gas turbine engine 10 is circumferentialiy disposed about an engine eenterline, or axial cersterline axis A.
  • the gas turbine engine 10 includes a fan 14 and a core engine 16.
  • An outer housing, nacelle 28 (or fan nacelle) extends circumferentialiy about the fan 14.
  • a fan bypass passage 32 extends between the nacelle 28 and an inner housing, engine cowl 34, which generally surrounds a low pressure compressor, a high pressure compressor, a low pressure turbine, and a high pressure turbine (all not illustrated here for simplicity, but well known in the art).
  • the fan 14 draws air into the gas turbine engine 10 as a core flow, C, and into the bypass passage 32 as a bypass air flow, D.
  • the bypass air flow D is discharged as a discharge flow through a fan nozzle 40 defined at the rear of the nacelle 28.
  • the fan nozzle exit area is thus defined by the position of the rear of the nacelle in relationship to the engine cowl 34.
  • Exemplary embodiments disclosed herein are operable to change the position of the rear of the nacelle relati ve to the engine co wl 34, and thus affect the fan nozzle exit area.
  • nacelle 28 mcludes a thrust reverser assembly 50, illustrated without the translatable cowl member in FIG, 2.
  • upper hinge beam 53 and lower latch beam 54 include slider tracks 58 or rails to support the translation of the translatable cowl member.
  • thrust reverser assembly 50 is a cascade type reverser employing a cascade structure 64, as is known in the art.
  • aft movement of the translatable cowl member along the slider tracks or rails uncovers the cascades 66 and opens a passage through which fan air is discharged in forward and outward directions.
  • One or more transcowl actuators (not shown in this view) are utilized to translate the translatable cowl- member between the stowed position and the deployed position.
  • translatable cowl member 52 is supported in a nominal stowed position during flight, and may be translated aft into one or more deployed positions after landing to allow fan air to be utilized for reverse thmst as discussed in the background section.
  • Thrust reverser assembly 50 may include any configuration which utilizes one or more translatable cowl members 52 able to translate forward and aft in a direction generally parallel to axis A .
  • translatable cowl member 52 may be supported in one or more "modified” stowed positions as discussed in greater detail below in order to provide variation in the fan nozzle area.
  • the slider tracks or rails 58 are mounted in movable relationship relative to its respective hinge or latch beam (hinge beam 53, shown).
  • a plurality of 4-bar linkages 60 is utilized with each slider track such that each of the slider tracks articulate responsive to a track actuator 62.
  • the 4-bar linkages may be arranged and coordinated such that activation of the track actuator causes articulation of the slider tracks and produces slight outward motion at the rear of the translatable co wl member, while minimizing movement of the forward region of the translatable cowl member.
  • the translatable cowl member remains in a stowed position relative to the slider tracks, but its position is slightly modified with respect to the core cowl 34.
  • the modified position of the translatable cowl member provides an opportunity for variation in the area of the fan nozzle 40 as illustrated in FIG. 3.
  • the fan nozzle area may be increased as compared to the fan nozzle area when the translatable cowl member is in the nominal stowed position, Movement of the track actuator(s) 62 may be modified to provide various modified positions of the translatable cowl member.
  • each slider track 58 up to five 4-bar linkages may be used for each slider track 58, in other embodiments, any suitable number of 4- bar linkages may be utilized for each slider track. It is envisioned that other mechanisms may be utilized to provide movement of the slider track 58 relative to its respective support member (upper or lower beam). Thus for a split transcowl that is supported on its upper and lower ends, four track actuators 62 having synchronized motion could be employed.
  • transcowl actuator 70 is illustrated. (Although shown as appearing to be floating, it is understood that the illustration shows an exemplary position of a transcowl actuator 70 understood to be coupled to the body of revolution of the transcowl). Those having skill in the art will appreciate that the transcowl actuator(s) 70 should accommodate the movement of the transcowl into the modified position(s) due to articulation of the slider tracks. It is envisioned, that, for example, transcowl actuators 70 may include a gimbal joint 72. Those having skill in the art will also appreciate that certain seals may be required to avoid overboard leakage at the slider tracks. [0029] FIG. 5 provides a side view of a slider track and one of the 4-bar linkages,

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention se rapporte à un ensemble de buse à jet plat variable comprenant un élément de capot monté sur une glissière. La glissière peut être articulée par rapport à l'élément de support pour modifier légèrement la position de l'élément de capot afin de varier la surface de sortie de la buse à jet plat. Au moins un quadrilatère articulé peut être utilisé pour permettre l'articulation de la glissière en réponse à la commande d'un actionneur. Un procédé permettant de varier la surface de sortie de la buse à jet plat comprend la fixation d'une première glissière de façon articulable par rapport à l'élément de support; la fixation d'un premier élément de capot de façon coulissante par rapport à une première glissière de sorte qu'une buse à jet plat soit au moins partiellement définie par une surface du premier élément de capot; la variation de la position opérationnelle du premier élément de capot en articulant la première glissière sans faire coulisser le premier élément de capot sur la première glissière pour varier la surface de sortie de la buse à jet plat.
EP11751969A 2010-02-15 2011-02-11 Glissière à articulation Withdrawn EP2536941A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US30474110P 2010-02-15 2010-02-15
PCT/US2011/024517 WO2011142866A2 (fr) 2010-02-15 2011-02-11 Glissière à articulation

Publications (1)

Publication Number Publication Date
EP2536941A2 true EP2536941A2 (fr) 2012-12-26

Family

ID=44545867

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11751969A Withdrawn EP2536941A2 (fr) 2010-02-15 2011-02-11 Glissière à articulation

Country Status (5)

Country Link
US (1) US20130202402A1 (fr)
EP (1) EP2536941A2 (fr)
JP (1) JP5782463B2 (fr)
CA (1) CA2789438A1 (fr)
WO (1) WO2011142866A2 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10247136B2 (en) 2015-12-03 2019-04-02 General Electric Company Thrust reverser system for a gas turbine engine

Family Cites Families (17)

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Publication number Priority date Publication date Assignee Title
DE1234099B (de) * 1965-09-15 1967-02-09 Gen Electric Ringfoermige konvergent-divergente Schubduese
US4132068A (en) * 1975-04-30 1979-01-02 The United States Of America As Represented By The United States National Aeronautics And Space Administration Variable area exhaust nozzle
US4184807A (en) * 1978-07-10 1980-01-22 Berg George W Reversible hydraulic engine
FR2457390A1 (fr) * 1979-05-23 1980-12-19 Europ Propulsion Divergent deployable de tuyere pour propulseur fusee
FR2496766A1 (fr) * 1980-12-23 1982-06-25 Snecma Dispositif de guidage de carenage mobile d'un systeme d'inversion de poussee
EP0109219A3 (fr) * 1982-11-12 1985-11-13 LUCAS INDUSTRIES public limited company Dispositif d'inversion de jet pour un moteur à turbine à gaz
JPH09195853A (ja) * 1995-12-14 1997-07-29 United Technol Corp <Utc> 可変面積ファンエキゾーストノズル
FR2748779B1 (fr) * 1996-05-15 1998-06-19 Hispano Suiza Sa Inverseur de poussee de turboreacteur a portes associees a un panneau amont
US6311928B1 (en) * 2000-01-05 2001-11-06 Stage Iii Technologies, L.C. Jet engine cascade thrust reverser for use with mixer/ejector noise suppressor
US6584763B2 (en) * 2001-08-01 2003-07-01 Rohr, Inc. Lock for the translating sleeve of a turbofan engine thrust reverser
FR2868131B1 (fr) * 2004-03-25 2006-06-09 Airbus France Sas Tuyere primaire a chevrons pour turboreacteur a double flux d'aeronef et aeronef comportant une telle tuyere
US7886518B2 (en) * 2006-11-14 2011-02-15 General Electric Company Turbofan engine cowl assembly and method of operating the same
US8127531B2 (en) * 2008-11-11 2012-03-06 The Boeing Company Radially translating fan nozzle nacelle
US8127532B2 (en) * 2008-11-26 2012-03-06 The Boeing Company Pivoting fan nozzle nacelle
US8443586B2 (en) * 2009-11-24 2013-05-21 United Technologies Corporation Variable area fan nozzle bearing track
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Also Published As

Publication number Publication date
JP5782463B2 (ja) 2015-09-24
WO2011142866A3 (fr) 2012-01-19
JP2013519823A (ja) 2013-05-30
US20130202402A1 (en) 2013-08-08
CA2789438A1 (fr) 2011-11-17
WO2011142866A2 (fr) 2011-11-17

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