EP1846295A1 - Conduit d'échappement d'unité d'alimentation auxiliaire avec silencieux intégrant un revêtement acoustique remplacable de l' extérieur - Google Patents

Conduit d'échappement d'unité d'alimentation auxiliaire avec silencieux intégrant un revêtement acoustique remplacable de l' extérieur

Info

Publication number
EP1846295A1
EP1846295A1 EP05801132A EP05801132A EP1846295A1 EP 1846295 A1 EP1846295 A1 EP 1846295A1 EP 05801132 A EP05801132 A EP 05801132A EP 05801132 A EP05801132 A EP 05801132A EP 1846295 A1 EP1846295 A1 EP 1846295A1
Authority
EP
European Patent Office
Prior art keywords
exhaust duct
cap
stinger
acoustic liner
aircraft
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Withdrawn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
EP05801132A
Other languages
German (de)
English (en)
Inventor
Nicholas A. Williams
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.)
Honeywell International Inc
Original Assignee
Honeywell International Inc
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
Priority claimed from US10/999,242 external-priority patent/US7448133B2/en
Application filed by Honeywell International Inc filed Critical Honeywell International Inc
Publication of EP1846295A1 publication Critical patent/EP1846295A1/fr
Withdrawn legal-status Critical Current

Links

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
    • B64D41/00—Power installations for auxiliary purposes
    • 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
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • 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
    • B64D41/00—Power installations for auxiliary purposes
    • B64D2041/002—Mounting arrangements for auxiliary power units (APU's)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N1/00—Silencing apparatus characterised by method of silencing
    • 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
    • F05D2220/50—Application for auxiliary power units (APU's)
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to an auxiliary power unit exhaust duct and, more particularly, to an exhaust duct incorporating an externally replaceable acoustic liner.
  • FIG. 1 shows a typical airborne APU 100 installed in the tailcone of an aircraft (shown in dashed outline 105).
  • Some of the key systems include an inlet system 110, a mounting system 115, a pneumatic system 120 and an exhaust system 125.
  • the exhaust system 125 performs many functions, including evacuating APU exhaust gas from the aircraft, attenuating exhaust noises, and providing compartment cooling airflow when used in conjunction with an eductor system.
  • the functional design aspects of these duties are often integrated into a single exhaust muffler system to reduce weight.
  • Unfortunately, the compromises between functionality, reliability, cost, and weight often result in an exhaust duct that will need repair work one or more times in its lifetime.
  • the component of the exhaust duct that will most often need repair, or rather replacement, is the acoustic liner. This is because the thermal cycling and harsh environment that the acoustic liner is exposed to makes it rather brittle and subject to cracking.
  • an exhaust duct may not lend itself to simple and straightforward repair methods for replacing an acoustic liner.
  • replacement of an acoustic liner typically requires removal of the APU 100 and exhaust system 125 from the aircraft, resulting in significant downtime for the operators of the aircraft.
  • an exhaust duct incorporating an externally replaceable acoustic liner.
  • the exhaust duct disclosed allows for an acoustic liner to be replaced on-wing, or from the outside of the aircraft, without removing the entire exhaust duct from the aircraft.
  • an exhaust duct is disclosed that includes a forward section, a body section, and a stinger cap with replaceable acoustic liner.
  • the forward section is configured to be axially coupled with a bulkhead collar on the aircraft.
  • the body section is coupled to the forward section and the stinger cap with replaceable acoustic liner is configured to be slideably received by the body section.
  • an auxiliary power unit exhaust duct for use in an aircraft includes a forward section, a body section, and a stinger cap with replaceable acoustic liner.
  • the forward section is configured to be axially coupled with a bulkhead collar on an aircraft and also includes a flow entrainment bellmouth.
  • the body section is coupled to the forward section and includes an outer skin with a plurality of baffles.
  • the stinger cap with replaceable acoustic liner is configured to be slideably received by the plurality of baffles of the body section.
  • the replaceable acoustic liner is also slideably coupled to the bellmouth.
  • a method of replacing an acoustic liner of an exhaust duct mounted in an aircraft includes uncoupling a stinger cap from the aircraft, the stinger cap having the acoustic liner and sliding the stinger cap with the acoustic liner out of the exhaust duct. Once the stinger cap is out, the acoustic liner is removed and a new acoustic liner is attached to the stinger cap. The stinger cap with the new acoustic liner is then inserted into the exhaust duct and coupled to the aircraft.
  • FIG. 1 shows a typical airborne auxiliary power unit installed in a tailcone of an aircraft
  • FIG. 2 shows a side view of one embodiment of an exhaust duct
  • FIG. 3 shows a front isometric view of the exhaust duct of FIG.2;
  • FIG. 4 is a rear isometric view of the exhaust duct in FIG. 2 showing how the stinger cap may be removed from the body section;
  • FIG. 5 is an isometric view showing an exhaust duct installed in a representative aircraft tailcone
  • FIG. 6 is a cross-sectional view taken at 6 in FIG. 3 showing the interfaces of the forward end cap
  • FIG. 7 is a cross-sectional view at 7 in FIG. 5 showing the exhaust duct and the interface with surrounding aircraft structure;
  • FIG. 8 shows a more detailed view of the baffles in FIG. 7;
  • FIG. 9 shows a more detailed view of the aft support area of the exhaust duct in FIG. 7.
  • the terms “comprises,” “comprising,” “includes,” “including,” “has,” “having” or any other variation thereof, are intended to cover a non-exclusive inclusion.
  • a process, method, article, or apparatus that comprises a list of elements is not necessarily limited to only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
  • "or” refers to an inclusive or and not to an exclusive or. For example, a condition A or B is satisfied by any one of the following: A is true (or present) and B is false (or not present), A is false (or not present) and B is true (or present), and both A and B are true (or present).
  • the present invention is directed to an exhaust duct that incorporates an externally replaceable acoustic liner that can be removed and replaced without removing the exhaust duct from the aircraft.
  • the exhaust duct incorporates into a single unit the functional details required to provide:
  • APU auxiliary power unit
  • FIG. 2 shows a side view and FIG. 3 shows a front isometric view of one embodiment of an exhaust duct 200 which includes a forward section 202, a body section 204, and an aft aircraft interface or stinger cap 206.
  • Each primary area of the exhaust duct 200 and the key features are described in detail in the following paragraphs.
  • a portion of outer skin 218 of the exhaust duct 200 has been cut away to reveal the acoustic liner 208 and one of the plurality of baffles 220 inside.
  • the various sections of the exhaust duct 200, and details therein, can be joined together by a number of means, including, but not limited to, welding, brazing, bonding, and fasteners, such as rivets, or bolts.
  • the exhaust duct 200 may use one or more of these methods to assemble the part.
  • FIG. 4 shows a rear isometric view of the exhaust duct 200 with the stinger cap 206 and acoustic liner 208 slid from the body section 204. This allows the removal and replacement of the acoustic liner 208 in an exhaust duct 200 that is replaceable on- wing, or from the outside of the aircraft.
  • FIG. 5 shows an isometric view of the exhaust duct 200 installed in a representative aircraft tailcone 210.
  • the forward section 202 of the exhaust duct 200 includes axially fixed mounting provisions 228 to allow the exhaust duct 200 to be installed in the aircraft, and a forward end cap 212.
  • the eductor components are a two piece bellmouth 214 and a flow inhibitor 216.
  • the bellmouth 214 is a formed sheet metal nozzle that allows the high energy APU exhaust gasses to entrain the APU compartment air into the exhaust flow to provide cooling for the APU compartment.
  • the two sections of the bellmouth have identical functional geometry in regards to flow and differ in that one section 214a is permanently fixed to the exhaust duct and one section 214b is attached by means of threaded fasteners. This allows the APU to be installed and removed from the aircraft without the need to remove the exhaust duct.
  • FIG. 6 is a cross-sectional view taken at 6 in FIG. 3 showing the interfaces of the forward end cap 212.
  • the forward end cap 212 a formed sheet metal component, provides footprint space for the axially fixed mounting provisions 228, and also provides attachment areas for the two bellmouth pieces and forms the envelope geometry of the forward portion of the exhaust duct.
  • the fixed bellmouth 214a piece is directly attached 230 to the forward end cap 212 by welding, riveting, or other suitable means.
  • the removable bellmouth piece 214b is attached to the forward end cap through ancillary brackets on the fixed bellmouth and on the forward end cap.
  • a circumferential lip is also provided on the forward end cap 212 to receive the removable bellmouth piece.
  • FIG. 7 is a cross sectional view at 7 in FIG. 5 showing the exhaust duct 200 and interface with surrounding aircraft structure.
  • the body section 204 of the exhaust duct 200 is primarily comprised of the muffler section that includes a plurality of baffles 220, the outer skin 218 of the exhaust duct, and the portion of the exhaust gas flow path formed by the acoustic liner 208.
  • the baffles 220 and outer skin 218 may be made of sheet metal.
  • the baffles 220 which are similar in shape to the forward end cap 212, and the outer skin 218 form the envelope geometry of the body section of the exhaust duct as well as define the acoustic cavity for the muffler.
  • FIG. 8 shows a more detailed view of the baffles in FIG. 7.
  • the joint 234 between the outer skin 218 and the baffles 220 can be riveted, welded, brazed, or any other suitable configuration.
  • the inside geometry of the baffles 220 matches that of the flow path of the exhaust duct and is often circular in shape.
  • the inside diameter of the baffles 220 is slightly larger than the outside diameter of the cylinder formed by the acoustic liner, this resulting in a small gap 236 between the baffles 220 and the acoustic liner 208.
  • This gap 236, which is sized based on the thermal growth properties of the acoustic liner 208 and the baffles 220, allows radial and axial thermal growth of the acoustic liner 208.
  • This gap 236 also allows the acoustic liner 208 to be slid into and out of the body section 204.
  • the acoustic liner 208 is positioned inside the body section 204 of the exhaust duct 200, it is not directly attached to any of the components of the body section 204.
  • the flow inhibitor 216 which ideally is a compressible seal around the outer skin 218 of the exhaust duct 200, is used when the exhaust duct 200 is installed in a compartment other than an APU compartment 260.
  • the bulkhead 222 that separates the APU compartment 260 and the exhaust duct compartment 262 will by necessity incorporate an opening to allow the eductor system to operate. To increase the efficiency of the eductor system, flow between the two compartments needs to be minimized.
  • a bulkhead collar 224 that matches the outer shape (circular, elliptical, etc.) of the exhaust duct 200 is typically the most cost and weight effective method of interfacing the bulkhead 222 and the exhaust duct 200.
  • This bulkhead collar 224 can easily accommodate 226 the axially fixed mounting provisions 228 as well as provide an effective interface for the flow inhibitor 216 to provide adequate flow separation between the two compartments. Being compressible, the flow inhibitor 216 also compensates for the radial thermal growth of the exhaust duct 200.
  • the axially fixed mounting provision accommodations 226 are arranged in an annular pattern relative to the bellmouth 214 on the forward end cap 212 of the exhaust duct.
  • the axially fixed mounting provisions 228 and the accommodations 226 on the bulkhead collar 224 receive threaded fasteners to transmit the exhaust duct loads into the aircraft structure.
  • the receiving devices for the fasteners which ideally are industry standard nutplates, are allowed to float radially within small slots cut into brackets which are attached to the forward end cap 212 of the exhaust duct (see FIG. 3). The use of these brackets allows the forward end cap 212 of the exhaust duct to remain free of openings, thereby further increasing the efficiency of the eductor system.
  • FIG. 9 shows a more detailed view of the exhaust duct 200 and aircraft structure in FIG. 7, which provides support not only for the body section 204 of the exhaust duct, but for the stinger cap section 206 as well.
  • the aft support structure must also accommodate the radial and axial thermal growth of the exhaust duct as a whole.
  • the aft support structure is comprised of two pieces, an aft end cap 238 and a compressible support seal 242 similar to the one used as the flow inhibitor 216.
  • the outermost geometry of the aft end cap 238 matches that of the outer skin 218 and is attached thereto by a similar means as for the forward end cap 212.
  • the aft end cap 238 provides a seal leg 240, the outside diameter of which accommodates the compressible support seal 242, while the inside diameter interfaces with a similar compressible seal 244 attached to the exhaust pipe 248 of the stinger cap 206.
  • the aircraft structure must supply a support frame 246 similar to that used to support the forward section of the exhaust duct, except that there is no need to accommodate any axially fixed mounting provisions.
  • the stinger cap 206 of the exhaust duct 200 is comprised of the acoustic liner 208, exhaust pipe 248, and structural skin member 250.
  • the acoustic liner 208 is made of acoustically permeable material such as feltmetal or perfmetal. Typically cylindrical in shape, the acoustic liner 208 runs the length of the muffler section of the exhaust duct 200, from just aft of the bellmouth 214 to just forward of the exhaust duct end cap 238. As previously discussed, the acoustic liner 208 does not directly fasten to the baffles 220 in the muffler, nor does it fasten at the forward end to the bellmouth 214.
  • the acoustic liner 208 is axially fixed at only one end, to the exhaust pipe 248 and is allowed to float at the other end over the bellmouth 214 to accommodate axial and radial thermal growth (see gap 254 in FIG. 7).
  • the exhaust pipe 248, which is of a shape similar to the acoustic liner 208 and of similar diametric dimensions, provides the flowpath from the muffler section of the exhaust duct to the outside of the aircraft.
  • the exhaust pipe 248 and acoustic liner 208 are joined by fixed or threaded fasteners 252 that allow for easy removal of the acoustic liner 208 from the exhaust pipe 248.
  • Attached circumferentially to the exhaust pipe 248 is compressible seal 244, similar to the flow inhibitor 216.
  • This compressible seal 244 interfaces with the seal leg 240 of the aft end cap 238 of the exhaust duct 200 to provide support for the exhaust pipe 248 and acoustic liner 208 while permitting thermal growth between the exhaust pipe 248 and aft end cap 238 of the exhaust duct.
  • Attached to the outer surface of this channel 256 is a structural skin member 250 that also matches the loft line of the aircraft utilizing the exhaust duct 200.
  • the structural skin member 250 extends forward from the exit plane of the exhaust pipe 248 to a support frame 246 on the aircraft.
  • This support frame 246 can be a dedicated frame for the support of the stinger cap 206 or it can be integrated into other support structures.
  • the structural skin member 250 may incorporate stiffening ribs as required to fully support the exhaust pipe 248 and acoustic liner 208.
  • the exhaust pipe 248, structural channel 256, and structural skin member 250 are attached to one another via rivets, welding, or any other suitable means capable of supporting the required loads of a particular application.
  • the structural skin member 250, and hence the entire stinger cap assembly 206 are attached to the support frame 246 via threaded fasteners 258.
  • the stinger cap 206 is the only component that needs to be removed.
  • the unique design disclosed for the exhaust duct 200 allows for removal of the acoustic liner 208 externally from the outside of the aircraft without removing the entire exhaust duct 200.
  • the acoustic liner 208 is part of the stinger cap 206, along with the exhaust pipe 248 and the structural skin member 250.
  • the threaded fasteners 258 holding the structural skin member 250 to the support frame 246 on the aircraft are removed.
  • the stinger cap 206 and acoustic liner 208 may then be slid out of the exhaust duct 200 (see FIG. 4). Once removed, the acoustic liner 208 may then be removed from the stinger cap 206 by unfastening fasteners 252 holding the acoustic liner 208 to the exhaust pipe 248. A new acoustic liner 208 may then be attached to the exhaust pipe 248 using fasteners 252. The stinger cap 206 with new acoustic liner 208 is then slid into the exhaust duct 200 on the aircraft and the structural skin member 250 is attached to the support frame 246 using threaded fasteners 258.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Exhaust Silencers (AREA)

Abstract

L’invention porte sur des procédés et un appareil pour conduit d’échappement (200) ayant un revêtement acoustique remplaçable de l’extérieur (208). Le conduit d’échappement (200) comporte une partie avant (202) configurée pour se coupler axialement avec un collier de cloison de séparation (224) sur l’avion, une partie corps (204) couplée à la partie avant (202) et un capuchon de poussoir (206) englobant le revêtement acoustique remplaçable (208). Le revêtement acoustique remplaçable (208) est configuré pour être reçu par glissement dans la partie corps (204).
EP05801132A 2004-09-23 2005-09-23 Conduit d'échappement d'unité d'alimentation auxiliaire avec silencieux intégrant un revêtement acoustique remplacable de l' extérieur Withdrawn EP1846295A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US61267504P 2004-09-23 2004-09-23
US10/999,242 US7448133B2 (en) 2004-09-23 2004-11-30 Procedure for replacement of acoustic liner in integrated exhaust duct muffler for use with airborne auxiliary power units
PCT/US2005/034188 WO2006034461A1 (fr) 2004-09-23 2005-09-23 Conduit d’échappement d’unité d’alimentation auxiliaire avec silencieux intégrant un revêtement acoustique remplaçable de l’extérieur

Publications (1)

Publication Number Publication Date
EP1846295A1 true EP1846295A1 (fr) 2007-10-24

Family

ID=35585687

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05801132A Withdrawn EP1846295A1 (fr) 2004-09-23 2005-09-23 Conduit d'échappement d'unité d'alimentation auxiliaire avec silencieux intégrant un revêtement acoustique remplacable de l' extérieur

Country Status (2)

Country Link
EP (1) EP1846295A1 (fr)
WO (1) WO2006034461A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007061995B4 (de) * 2007-12-21 2012-03-01 Airbus Operations Gmbh Vorrichtung zum mechanisch entkoppelten Befestigen einer von Heißgas durchströmten Flugzeugkomponente
FR3059301B1 (fr) * 2016-11-29 2018-12-07 Safran Power Units Systeme d'echappement d'un moteur auxiliaire de puissance

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4137992A (en) * 1976-12-30 1979-02-06 The Boeing Company Turbojet engine nozzle for attenuating core and turbine noise
JP2000516553A (ja) * 1996-08-02 2000-12-12 アライド・シグナル・インコーポレーテツド 一体化された着脱可能な航空テイルコーン装置
US6615576B2 (en) * 2001-03-29 2003-09-09 Honeywell International Inc. Tortuous path quiet exhaust eductor system
ES2224807B1 (es) * 2002-08-14 2007-05-01 Sener, Ingenieria Y Sistemas, S.A. Conducto de reduccion de ruido para componentes estaticos de motores aeronauticos.

Non-Patent Citations (1)

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Title
See references of WO2006034461A1 *

Also Published As

Publication number Publication date
WO2006034461A1 (fr) 2006-03-30

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