US20010002537A1 - Nozzle - Google Patents

Nozzle Download PDF

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Publication number
US20010002537A1
US20010002537A1 US09/725,948 US72594800A US2001002537A1 US 20010002537 A1 US20010002537 A1 US 20010002537A1 US 72594800 A US72594800 A US 72594800A US 2001002537 A1 US2001002537 A1 US 2001002537A1
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United States
Prior art keywords
nozzle
primary
angle
nozzles
engine
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Granted
Application number
US09/725,948
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US6415598B2 (en
Inventor
Richard Pinker
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.)
Rolls Royce PLC
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UK Secretary of State for Defence
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Filing date
Publication date
Application filed by UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Assigned to SECRETARY OF STATE FOR DEFENCE, THE reassignment SECRETARY OF STATE FOR DEFENCE, THE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PINKER, RICHARD A.
Publication of US20010002537A1 publication Critical patent/US20010002537A1/en
Assigned to QINETIQ LIMITED reassignment QINETIQ LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SECRETARY OF STATE FOR DEFENCE, THE
Application granted granted Critical
Publication of US6415598B2 publication Critical patent/US6415598B2/en
Assigned to ROLLS-ROYCE PLC reassignment ROLLS-ROYCE PLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: QINETIQ LIMITED
Adjusted expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F02K1/46—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
    • 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
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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 invention relates to arrangement of the propulsion nozzles for gas turbine engines in particular to by-pass gas turbine engines.
  • U.S. Pat. No. 4,288,984 discloses a number of ways in which the mixing and distribution of the exhaust jet plumes is controlled in a by-pass engine. These include having a swept, canted or off-set primary nozzle.
  • the invention comprises a by-pass gas turbine engine including a primary and a secondary nozzle wherein the primary nozzle is situated radially within, but axially protruding from, the secondary nozzle characterised in that the primary and secondary nozzles have a substantially common central axis along their lengths and that the direction of airflow exiting at least one of the primary or secondary nozzles is at an angle to the central axis of the engine and the direction of airflow exiting each nozzle is at an angle to the other thereby promoting preferential distribution and mixing of the airflows.
  • both the primary and secondary nozzles are truncated at oblique angles.
  • the nozzles are preferably orientated such that said oblique angles are opposite directions.
  • the exit plane of the airflow is therefore not perpendicular to the central axis defined by the nozzle.
  • the flow direction of the primary nozzle axis is simply orientated at a small angle to the axis of the secondary nozzle.
  • the internal profile of one or both nozzles is asymmetric such that the primary flow exits the nozzle at an angle to the secondary flow.
  • FIG. 1 shows a scarfed nozzle arrangement according to one aspect of the invention.
  • FIG. 2 shows a schematic cross-section of a nozzle according to the invention.
  • FIG. 1 shows an arrangement of primary and secondary nozzles, denoted 1 and 2 respectively, of a by-pass gas turbine engine. Both of these nozzle have oblique “cut-off ends” 3, 4 i.e. they are truncated at angles of ⁇ and ⁇ relative to the perpendicular of the longitudinal axis of the nozzles—the common central axis 5 . The direction of the cut-offs are opposite with respect to the central axis 5 .
  • the oblique cut-off edge in elevation of the primary nozzle faces upwards and the oblique cut-off end of the secondary nozzle faces downwards.
  • the angles ⁇ and ⁇ lie in the range 0.5°to 30°.
  • the general direction of air flow from the primary nozzle is in the direction of the long arrows and the short arrow indicates the general direction of air flow from the secondary nozzle.
  • the quantities and direction of airflows is such that the overall momentum of airflow in an axis perpendicular to the engine axis is zero; i.e. the non axial airflows from the primary and secondary nozzles cancel each other.
  • FIG. 2 shows a schematic cross-section of a nozzle 10 according to the invention.
  • the nozzle 10 may be incorporated as either or both of the primary or secondary nozzles.
  • the shape and geometry of the nozzle wall is such that the general or average direction of overall air flow 11 is at an angle, ⁇ to the central nozzle axis 12 , when the central nozzle axis 12 is taken to be perpendicular to the end face 13 of the nozzle.

Abstract

A by-pass gas turbine engine including a primary and a secondary nozzle which are substantially convergent, wherein the primary nozzle is situated radially within, but axially protruding from, the secondary nozzle characterized in that the primary and secondary nozzles have a substantially common central axis along their lengths and the direction of airflow exiting at least one of the primary or secondary nozzles is at an angle to the central axis of the engine and that the direction of airflow exiting each nozzle is at an angle to the other thereby promoting preferential distribution and mixing of the airflows. The end of both the primary and secondary nozzles may be truncated at oppositely orientated oblique angles. The internal profile of one or both nozzles may be arranged such that the airflow leaves the that nozzle at an angle to the axis of the nozzle.

Description

  • The invention relates to arrangement of the propulsion nozzles for gas turbine engines in particular to by-pass gas turbine engines. [0001]
  • Control of the mixing and distribution of the exhaust jet plumes can be used to reduce the noise from gas turbine engines. Several methods have been tried to effect this and have resulted in differing degrees of effectiveness. Most methods result in significant thrust losses or increased weight. [0002]
  • U.S. Pat. No. 4,288,984 discloses a number of ways in which the mixing and distribution of the exhaust jet plumes is controlled in a by-pass engine. These include having a swept, canted or off-set primary nozzle. [0003]
  • It is an object of the invention to provide an improved nozzle design for by-pass engines which offers a significant reduction in noise while maintaining high efficiency. [0004]
  • The invention comprises a by-pass gas turbine engine including a primary and a secondary nozzle wherein the primary nozzle is situated radially within, but axially protruding from, the secondary nozzle characterised in that the primary and secondary nozzles have a substantially common central axis along their lengths and that the direction of airflow exiting at least one of the primary or secondary nozzles is at an angle to the central axis of the engine and the direction of airflow exiting each nozzle is at an angle to the other thereby promoting preferential distribution and mixing of the airflows. [0005]
  • This promotes mixing and dilution of the airflow and shielding the higher velocity jet by a greater proportion of the bypass flow, causing the noise to be convected to angles closer to the engine axis. [0006]
  • In one embodiment of the invention both the primary and secondary nozzles are truncated at oblique angles. The nozzles are preferably orientated such that said oblique angles are opposite directions. The exit plane of the airflow is therefore not perpendicular to the central axis defined by the nozzle. [0007]
  • In an alternative embodiment the flow direction of the primary nozzle axis is simply orientated at a small angle to the axis of the secondary nozzle. [0008]
  • In a further embodiment of the invention the internal profile of one or both nozzles is asymmetric such that the primary flow exits the nozzle at an angle to the secondary flow. [0009]
  • By way of example, the invention will now be described with reference to the drawings of which: [0010]
  • FIG. 1 shows a scarfed nozzle arrangement according to one aspect of the invention. [0011]
  • FIG. 2 shows a schematic cross-section of a nozzle according to the invention. [0012]
  • FIG. 1 shows an arrangement of primary and secondary nozzles, denoted [0013] 1 and 2 respectively, of a by-pass gas turbine engine. Both of these nozzle have oblique “cut-off ends” 3, 4 i.e. they are truncated at angles of α and β relative to the perpendicular of the longitudinal axis of the nozzles—the common central axis 5. The direction of the cut-offs are opposite with respect to the central axis 5. In the example, the oblique cut-off edge in elevation of the primary nozzle faces upwards and the oblique cut-off end of the secondary nozzle faces downwards. The angles α and β lie in the range 0.5°to 30°.
  • In operation the general direction of air flow from the primary nozzle is in the direction of the long arrows and the short arrow indicates the general direction of air flow from the secondary nozzle. The quantities and direction of airflows is such that the overall momentum of airflow in an axis perpendicular to the engine axis is zero; i.e. the non axial airflows from the primary and secondary nozzles cancel each other. [0014]
  • FIG. 2 shows a schematic cross-section of a nozzle [0015] 10 according to the invention. The nozzle 10 may be incorporated as either or both of the primary or secondary nozzles. The shape and geometry of the nozzle wall is such that the general or average direction of overall air flow 11 is at an angle, φ to the central nozzle axis 12, when the central nozzle axis 12 is taken to be perpendicular to the end face 13 of the nozzle.

Claims (5)

1. A by-pass gas turbine engine including a primary and a secondary nozzle wherein the primary nozzle is situated radially within, but axially protruding from, the secondary nozzle characterised in that the primary and secondary nozzles have a substantially common central axis along their lengths and the direction of airflow exiting at least one of the primary or secondary nozzles is at an angle to the central axis of the engine and that the direction of airflow exiting each nozzle is at an angle to the other thereby promoting preferential distribution and mixing of the airflows.
2. An engine as claimed in
claim 1
 wherein the end of both the primary and secondary nozzles are truncated at oblique angles and oriented such that said oblique angles are oppositely orientated.
3. An engine as claimed in
claims 2
 to
4
 wherein said oblique angle is in the range 0.5°to 30°.
4. An engine as claimed in
claim 1
 wherein the internal profile of one or both nozzles is arranged such that the airflow leaves the that nozzle at an angle to the axis of the nozzle, said axis taken to be perpendicular to end face of the nozzle.
5. An engine as substantially hereinbefore described with reference the accompanying drawings.
US09/725,948 1999-12-01 2000-11-30 Exhaust nozzle for by-pass gas turbine engines Expired - Lifetime US6415598B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB9928349 1999-12-01
GB9928349.1 1999-12-01
GB9928349A GB2356897B (en) 1999-12-01 1999-12-01 Improved nozzle

Publications (2)

Publication Number Publication Date
US20010002537A1 true US20010002537A1 (en) 2001-06-07
US6415598B2 US6415598B2 (en) 2002-07-09

Family

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US09/725,948 Expired - Lifetime US6415598B2 (en) 1999-12-01 2000-11-30 Exhaust nozzle for by-pass gas turbine engines

Country Status (5)

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US (1) US6415598B2 (en)
EP (1) EP1104847B1 (en)
CA (1) CA2327166A1 (en)
DE (1) DE60034531T2 (en)
GB (1) GB2356897B (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6596541B2 (en) 2000-10-31 2003-07-22 Regeneron Pharmaceuticals, Inc. Methods of modifying eukaryotic cells
US7293401B2 (en) * 2002-03-20 2007-11-13 The Regents Of The University Of California Jet engine noise suppressor
US7377108B2 (en) 2004-04-09 2008-05-27 The Boeing Company Apparatus and method for reduction jet noise from single jets
US7377109B2 (en) 2004-04-09 2008-05-27 The Boeing Company Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flows
FR2896772B1 (en) * 2006-01-27 2008-04-25 Snecma Sa SYSTEM FOR EJECTING A DOUBLE FLOW TURBOREACTOR
US7900433B2 (en) * 2006-08-31 2011-03-08 United Technologies Corporation Fan exhaust nozzle for turbofan engine
US7966825B2 (en) * 2006-10-31 2011-06-28 Honeywell International Inc. Exhaust eductor system with a recirculation baffle
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
FR2981126B1 (en) * 2011-10-06 2015-02-27 Snecma ASYMMETRIC TUYERE OF TURBOMACHINE
US20150330254A1 (en) * 2014-05-15 2015-11-19 United Technologies Corporation Compact Nacelle With Contoured Fan Nozzle
DE102017115644A1 (en) * 2017-07-12 2019-01-17 Rolls-Royce Deutschland Ltd & Co Kg Turbofan
US11306681B2 (en) 2019-01-15 2022-04-19 The Boeing Company Sheared exhaust nozzle

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4280587A (en) * 1979-05-08 1981-07-28 The Boeing Company Noise-suppressing jet engine nozzles and method
US4288984A (en) * 1978-09-19 1981-09-15 The Boeing Company Noise suppressing turbofan nozzles and method
US5924632A (en) * 1996-05-02 1999-07-20 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Jet nozzle having centerbody for enhanced exit area mixing
US6314721B1 (en) * 1998-09-04 2001-11-13 United Technologies Corporation Tabbed nozzle for jet noise suppression

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB868072A (en) * 1957-05-13 1961-05-17 Geoffrey Michael Lilley Improvements in or relating to jet noise suppression means
GB1110154A (en) * 1966-04-05 1968-04-18 Rolls Royce Aircraft jet power plant
US3881315A (en) * 1973-03-19 1975-05-06 Gen Electric Fan duct flow deflector
US3830431A (en) * 1973-03-23 1974-08-20 Nasa Abating exhaust noises in jet engines
US3997132A (en) * 1974-12-11 1976-12-14 The Garrett Corporation Method and apparatus for controlling tip vortices
US4254620A (en) * 1978-02-27 1981-03-10 The Boeing Company Jet engine multiduct noise suppressor
GB2075447B (en) * 1980-04-30 1983-10-26 Rolls Royce Thrust deflectors for gas turbine engines
FR2643947B1 (en) * 1989-03-01 1991-05-17 Snecma AXISYMMETRICAL NOZZLE TURBOREACTOR EJECTION ASSEMBLY WITH VARIABLE SECTION AND PUSH-THROUGH

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4288984A (en) * 1978-09-19 1981-09-15 The Boeing Company Noise suppressing turbofan nozzles and method
US4280587A (en) * 1979-05-08 1981-07-28 The Boeing Company Noise-suppressing jet engine nozzles and method
US5924632A (en) * 1996-05-02 1999-07-20 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Jet nozzle having centerbody for enhanced exit area mixing
US6314721B1 (en) * 1998-09-04 2001-11-13 United Technologies Corporation Tabbed nozzle for jet noise suppression

Also Published As

Publication number Publication date
EP1104847B1 (en) 2007-04-25
GB9928349D0 (en) 2000-01-26
GB2356897A (en) 2001-06-06
US6415598B2 (en) 2002-07-09
DE60034531T2 (en) 2007-12-27
EP1104847A3 (en) 2004-01-14
EP1104847A2 (en) 2001-06-06
CA2327166A1 (en) 2001-06-01
GB2356897B (en) 2003-05-14
DE60034531D1 (en) 2007-06-06

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