CA2648765A1 - Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods - Google Patents

Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods Download PDF

Info

Publication number
CA2648765A1
CA2648765A1 CA2648765A CA2648765A CA2648765A1 CA 2648765 A1 CA2648765 A1 CA 2648765A1 CA 2648765 A CA2648765 A CA 2648765A CA 2648765 A CA2648765 A CA 2648765A CA 2648765 A1 CA2648765 A1 CA 2648765A1
Authority
CA
Canada
Prior art keywords
pylon
projection
flow
projections
perimeter
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.)
Granted
Application number
CA2648765A
Other languages
French (fr)
Other versions
CA2648765C (en
Inventor
Vinod G. Mengle
Russell H. Thomas
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.)
Boeing Co
Original Assignee
Boeing 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 Boeing Co filed Critical Boeing Co
Publication of CA2648765A1 publication Critical patent/CA2648765A1/en
Application granted granted Critical
Publication of CA2648765C publication Critical patent/CA2648765C/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B64D33/06—Silencing exhaust or propulsion jets
    • 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
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F02K1/48—Corrugated nozzles

Abstract

Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections.

Claims (12)

1. An aircraft system, comprising:
a pylon (207) having a first side and a second side facing opposite the first side;
and a jet engine exhaust nozzle (220) carried by the pylon (207) and having an internal flow surface (232) adjacent a hot exhaust flow path, the internal flow surface (232) having an exit aperture (233) with a perimeter (234) that includes multiple projections (235) extending in an aft direction and circumferentially spaced about the perimeter (234), with a geometric feature of the multiple projections (235) changing in a monotonic manner along at least a portion of the perimeter (234), wherein a first projection nearest the first side of the pylon (207) and a second projection nearest the second side of the pylon (207) are both oriented inwardly into the flow path by a greater amount than the remaining projections.
2. The system of claim 1 wherein at least a portion of the first projection is positioned circumferentially outwardly from the first side of the pylon (207) and at least a portion of the second projection is positioned circumferentially outwardly from the second side of the pylon (207).
3. The system of claims 1 or 2 wherein the pylon (207) includes a heat shield (1109) having a first edge proximate to the first side of the pylon (207) and a second edge proximate to the second side of the pylon (207), and wherein at least a portion of the first projection is positioned circumferentially outwardly from the first edge of the heat shield (1109) and at least a portion of the second projection is positioned circumferentially outwardly from the second edge of the heat shield (1109).
4. The system of any of claims 1-3 wherein:
each of the first and second projections (235) has a generally triangular shape with a root (1126) and a tip (1125);
the root (1126) of the first projection has a first orientation relative to the first side of the pylon (207); and the root of the second projection has a second orientation relative to the second side of the pylon (207) that generally mirrors the first orientation.
5. The system of any of claims 1-4 wherein the root (1126) of the first projection is offset from the first side of the pylon (207) by a first angle in a first direction, and wherein the root of the second projection is offset from the second side of the pylon (207) by a second angle generally the same as the first angle in a second direction generally opposite the first direction.
6. The system of any of claims 1-5 wherein the tip (1125) of the first projection is offset from the first side of the pylon (207) by a first value in a first direction, and wherein the tip of the second projection is offset from the second side of the pylon (207) by a second value generally the same as the first value in a second direction generally opposite the first direction.
7. The system of any of claims 1-6 wherein the first projection is inclined radially inwardly into the flow by a greater amount than is a neighboring projection located circumferentially outwardly from the first projection.
8. The system of any of claims 1-7 wherein the first projection has a greater axial extent than does a neighboring projection located circumferentially outwardly from the first projection.
9. A method for operating an aircraft engine, comprising:
directing a flow of hot exhaust gas from an aircraft engine through an exhaust nozzle exit aperture (233), the aperture having a perimeter (234) with axially extending projections (235) arranged around the perimeter (234), and with a geometric feature of the projections (235) changing in a monotonic manner along at least a portion of the perimeter (234); and controlling the flow of hot exhaust gas near a pylon (207) supporting the engine by directing the flow adjacent to first and second projections (235) located at least partially outwardly from and nearest to oppositely facing sides of the pylon (207), the first and second projections (235) being oriented inwardly into the flow by a greater amount than are the remaining projections.
10. The method of claim 9 wherein controlling the flow includes at least restricting the hot flow from passing adjacent to the side of the pylon (207).
11. The method of claim 9 wherein controlling the flow includes entraining air from an adjacent flow of cooler bypass air by at a greater rate near the pylon (207) than at other circumferential locations around the nozzle exit aperture (233).
12. The method of claim 9 wherein controlling the flow includes increasing an axial vorticity component of the flow near the pylon (207) or a heat shield (1109) carried by the pylon (207) compared with an axial vorticity component of the flow at other circumferential locations around the nozzle exit aperture (233).
CA2648765A 2008-08-11 2008-08-11 Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods Active CA2648765C (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2008/072795 WO2010019131A1 (en) 2008-08-11 2008-08-11 Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods

Publications (2)

Publication Number Publication Date
CA2648765A1 true CA2648765A1 (en) 2010-02-11
CA2648765C CA2648765C (en) 2011-04-19

Family

ID=40380389

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2648765A Active CA2648765C (en) 2008-08-11 2008-08-11 Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods

Country Status (2)

Country Link
CA (1) CA2648765C (en)
WO (1) WO2010019131A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9511873B2 (en) 2012-03-09 2016-12-06 The Boeing Company Noise-reducing engine nozzle system

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8746613B2 (en) 2008-08-20 2014-06-10 Williams International Co., L.L.C. Jet engine exhaust nozzle and associated system and method of use
DE102010045697A1 (en) * 2010-09-16 2012-03-22 Rolls-Royce Deutschland Ltd & Co Kg Flower mixer for a turbofan engine
GB2492311B (en) 2011-05-20 2015-01-28 Dhayan Tomas Ishigaki Periorbital edema reduction
DE102012220360A1 (en) * 2012-11-08 2014-05-08 Rolls-Royce Deutschland Ltd & Co Kg Nozzle with guide devices
FR3012417B1 (en) * 2013-10-31 2016-12-09 Snecma TURBOREACTOR NACELLE

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1127659A (en) * 1966-09-16 1968-09-18 Rolls Royce Improvements in gas turbine engines
GB2146702B (en) * 1983-09-14 1987-12-23 Rolls Royce Exhaust mixer for turbofan aeroengine
US6360528B1 (en) * 1997-10-31 2002-03-26 General Electric Company Chevron exhaust nozzle for a gas turbine engine
US6314721B1 (en) * 1998-09-04 2001-11-13 United Technologies Corporation Tabbed nozzle for jet noise suppression
WO2000053915A1 (en) * 1999-03-05 2000-09-14 Rolls-Royce Deutschland Gmbh Bloom mixer for a turbofan engine
US6983912B2 (en) * 2002-04-30 2006-01-10 The Boeing Company Hybrid exhaust heat shield for pylon mounted gas turbine engines
FR2855558B1 (en) * 2003-05-28 2005-07-15 Snecma Moteurs TURBOMACHINE TUBE WITH NOISE REDUCTION
GB0505246D0 (en) * 2005-03-15 2005-04-20 Rolls Royce Plc Engine noise
US7520124B2 (en) * 2006-09-12 2009-04-21 United Technologies Corporation Asymmetric serrated nozzle for exhaust noise reduction

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9511873B2 (en) 2012-03-09 2016-12-06 The Boeing Company Noise-reducing engine nozzle system

Also Published As

Publication number Publication date
WO2010019131A1 (en) 2010-02-18
CA2648765C (en) 2011-04-19

Similar Documents

Publication Publication Date Title
EP3211319B1 (en) A combustion chamber
US7597537B2 (en) Thermal control of gas turbine engine rings for active clearance control
US20100146980A1 (en) masking arrangement for a gas turbine engine
US7637716B2 (en) Platform cooling arrangement for the nozzle guide vane stator of a gas turbine
CA2648765A1 (en) Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods
US9982890B2 (en) Combustor dome heat shield
US9810081B2 (en) Cooled conduit for conveying combustion gases
EP2959146B1 (en) Turbofan engine including third flowpath exhaust nozzle
CA2592676A1 (en) Jet engine nozzle exit configurations and associated systems and methods
US9909761B2 (en) Combustor wall assembly for a turbine engine
US20130152591A1 (en) System of integrating baffles for enhanced cooling of cmc liners
CA2624425A1 (en) Ring seal system with reduced cooling requirements
EP3091192B1 (en) Blade outer air seals with channels
GB2390345A (en) Exhaust heat shield for pylon mounted gas turbine engines includes cast and non-cast sections
EP1930550A3 (en) Systems for cooling integral turbine nozzle and shroud assemblies
CA2897377C (en) Combustor heat shield
US20160123186A1 (en) Shroud assembly for a turbine engine
CN107143385A (en) A kind of gas turbine guider leading edge installs side structure and the gas turbine with it
US20050241321A1 (en) Transition duct apparatus having reduced pressure loss
US10794329B2 (en) Exhaust plume cooling using periodic interruption of exhaust gas flow to form ambient air entraining vortices
US9027323B2 (en) Bloom mixer for a turbofan engine
EP2921684B1 (en) Integrated primary nozzle
EP3441593B1 (en) Lobed gas discharge fairing for a turbofan engine
US9810434B2 (en) Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US10227952B2 (en) Gas path liner for a gas turbine engine

Legal Events

Date Code Title Description
EEER Examination request