GB2610451A - Turbofan engine efficient ducting - Google Patents

Turbofan engine efficient ducting Download PDF

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Publication number
GB2610451A
GB2610451A GB2200531.8A GB202200531A GB2610451A GB 2610451 A GB2610451 A GB 2610451A GB 202200531 A GB202200531 A GB 202200531A GB 2610451 A GB2610451 A GB 2610451A
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GB
United Kingdom
Prior art keywords
ducting
computational
judgement means
turbofan engine
efficient
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
GB2200531.8A
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GB2610451B (en
Inventor
Lynley Ashley Adrian
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Individual
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Individual
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Publication date
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Priority to GB2200531.8A priority Critical patent/GB2610451B/en
Publication of GB2610451A publication Critical patent/GB2610451A/en
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Publication of GB2610451B publication Critical patent/GB2610451B/en
Active 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
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/057—Control or regulation
    • 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
    • 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
    • F02K1/15—Control or regulation
    • F02K1/16—Control or regulation conjointly with another control
    • F02K1/165—Control or regulation conjointly with another control with air intake control
    • 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
    • F02K1/30—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 varying effective area of 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
    • F02K1/38—Introducing air inside the jet
    • 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
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer

Abstract

A turbofan engine bypass ducting with radially inlet guide apertures 1 controllable by at least one computational judgement means 3 to regulate air flow into the inner ducting, forming a boundary layer on the inside of the duct, reducing main fan airflow adhesion, increasing efficiency, configuring dynamic acceleration surfaces 2 size such that inflow air is accelerated over the inner ducting surface, optimised by the computational judgement means using data from a plurality of airspeed sensors 4 and plurality of environmental sensors 5, such as altitude and atmospheric barometric pressure and temperature. Optionally, the computational judgement means has adaptable learning capabilities. Optionally the ducting can be applied to an electric ducted fan or biofuel gas turbine engine. Optionally the aperture guide means may direct inlet airflow in a clockwise or anticlockwise spiral to match the angular rotation of the high bypass or exhaust nozzle.

Description

TURBOFAN ENGINE EFFICIENT DUCTING
FIELD OF THE INVENTION
This invention relates to a turbofan engine efficient ducting with a controllable variable inlet venting.
BACK GROUND OF THE INVENTION
This invention relates to a turbofan engine efficient ducting such that the external air is sucked into the ducting enhancing the inner boundary layer of the ducting such that the bypass air speed is increased efficiency of the turbofan gas turbine jet engine.
At present on conventional turbo fan engine on commercial passenger airlines there is no efficient ducting. Moreover passenger airline on a long haul flight would subsequently benefit from a more efficient ducting with and increase of bypass air flow velocity by an estimated projected 10.5% gain. Any performance gain will translate into a faster passenger transit time to their destination. In addition to efficient fuel usage and a reduction to the impact on the atmosphere and damage to the Earth atmosphere. Any increase to the performance of turbofan jet engine can only support a sustainable environment on Earth.
STATEMENT OF INVENTION
To enable more efficient ducting with and increase of bypass air flow velocity and core nozzle velocity of turbofan jet engine and increase the efficiency of the jet engine. The present invention proposes a turbofan engine efficient ducting with a controllable plurality radially inlet guide apertures and controllable dynamic acceleration surfaces.
An turbofan engine efficient ducting comprising an plurality radially inlet guide apertures, a dynamic acceleration surfaces, a computational judgement means, a plurality of airspeed sensors and a plurality of environment sensors
ADVANTAGES
The turbofan engine efficient ducting generated an enhanced boundary layer from the ingested extremal air increasing the efficiency of the airflow increase the efficiency of the engine and reducing the detrimental effect on the Earth atmosphere and reducing the transit time of the passenger airlines.
Preferably, the computational judgement means is provided by a digital computer with adaptable learning capabilities to make adjustments in varying operational conditions and environments.
Preferably, the a dynamic acceleration surfaces is adjustable for optimised efficient in any operating environment in terms of atmospheric pressure at different attitudes such that the efficient inner boundary layer is maintained.
BRIEF DESCRIPTION OF THE DRAWINGS
For a better understanding of the invention, an embodiment of the invention will now be described by way of a non-limiting example with reference to the accompanying drawing which: Fig 1. Shows a cross section view of the turbofan engine efficient ducting DETAILED DESCRIPTION OF THE INVENTION The following description is a preferred embodiment of the turbofan engine efficient ducting. The description does not limit the application exclusively to the aviation industry.
A plurality radially inlet guide apertures 1 are controlled by at least one computational judgement 3 means regulating the air inflow to the inner ducting forming a boundary layer on the inside of the duct reducing the adhesion of the main air flow from the main fan of a turbofan jet engine such that the efficiency is increased a dynamic acceleration surfaces 2 configuration size such that the inflow air is accelerated over the inner surface of the ducting is optimised by the said at least one computational judgement 3 means using the data from a plurality of airspeed sensors 4 and plurality of environment sensors 5 such as altitude and atmospheric barometric pressure and temperature.
The plurality radially inlet guide apertures 1 may also be applied to the exhaust gas nozzle of any gas turbine.

Claims (8)

  1. Claims 1. A turbofan engine efficient ducting comprising: A plurality radially inlet guide apertures are controlled by at least one computational judgement means regulating the air inflow to the inner ducting forming a boundary layer on the inside of the duct reducing the adhesion of the main air flow from the main fan of a turbofan jet engine such that the efficiency is increased a dynamic acceleration surfaces configuration size such that the inflow air is accelerated over the inner surface of the ducting is optimised by the said at least one computational judgement means using the data from a plurality of airspeed sensors and plurality of environment sensors such as altitude and atmospheric barometric pressure and temperature.
  2. 2. A turbofan engine efficient ducting according to claim 1 in which the said computational judgement means controls the aperture of the said plurality radially inlet guide apertures from data from said plurality of airspeed sensors and said plurality of environment sensors such as altitude and atmospheric barometric pressure and temperature to achieve maximum efficiency of the jet engine.
  3. 3. A turbofan engine efficient ducting according to claim 1 in which the said computational judgement means controls the dynamic acceleration surfaces configuration size such that the inflow air is accelerated over the inner surface of the ducting using from data from said plurality of airspeed sensors and said plurality of environment sensors such as altitude and atmospheric barometric pressure and temperature to achieve maximum efficiency of the jet engine.
  4. 4. A turbofan engine efficient ducting according to claim 1 in which the computational judgement means has adaptable learning capabilities to make adjustments to the controls in varying operational conditions and environments.
  5. 5. A turbofan engine efficient ducting according to claim 1 in which the computational judgement means has adaptable learning capabilities to make adjustments to the said dynamic acceleration surfaces configuration size and said plurality radially inlet guide apertures in response to varying operational conditions and environments.
  6. 6. A turbofan engine efficient ducting according to claim 1 is preferably applied to high bypass turbofan jet engines used on commercial passenger airlines or any type of jet engine or applied to electric ducted fan engines or biofuel gas turbines.
  7. 7. A turbofan engine efficient ducting according to claim 1 and claim 6 can also be applied to the exhaust gas nozzle of any type of gas turbine.
  8. 8. A turbofan engine efficient ducting according to claim 1 and claim 6 and claim 7 said plurality radially inlet guide apertures configured by said computational judgement means controls the aperture guide means such that the inlet airflow is directed in either a clock wise or anticlockwise spiral to match the angular rotation of either the high bypass of a gas turbine engine or exhaust nozzle such that the efficiency is increased.
GB2200531.8A 2022-01-18 2022-01-18 Turbofan engine efficient ducting Active GB2610451B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2200531.8A GB2610451B (en) 2022-01-18 2022-01-18 Turbofan engine efficient ducting

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2200531.8A GB2610451B (en) 2022-01-18 2022-01-18 Turbofan engine efficient ducting

Publications (2)

Publication Number Publication Date
GB2610451A true GB2610451A (en) 2023-03-08
GB2610451B GB2610451B (en) 2024-01-03

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117685098A (en) * 2024-02-01 2024-03-12 西安航空学院 Stepless adjusting device for outer duct of variable-cycle engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5826794A (en) * 1997-02-28 1998-10-27 The Boeing Company Aircraft scoop ejector nozzle
US20080092548A1 (en) * 2006-10-20 2008-04-24 United Technologies Corporation Gas turbine engine having slim-line nacelle
EP2204568A2 (en) * 2008-12-31 2010-07-07 Rolls-Royce Corporation Gas turbine engine with ejector and corresponding operating method
EP2410165A2 (en) * 2010-07-19 2012-01-25 United Technologies Corporation Gas turbine with noise attenuating variable area fan nozzle
WO2015026417A2 (en) * 2013-05-31 2015-02-26 General Electric Company Dual-mode plug nozzle

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5826794A (en) * 1997-02-28 1998-10-27 The Boeing Company Aircraft scoop ejector nozzle
US20080092548A1 (en) * 2006-10-20 2008-04-24 United Technologies Corporation Gas turbine engine having slim-line nacelle
EP2204568A2 (en) * 2008-12-31 2010-07-07 Rolls-Royce Corporation Gas turbine engine with ejector and corresponding operating method
EP2410165A2 (en) * 2010-07-19 2012-01-25 United Technologies Corporation Gas turbine with noise attenuating variable area fan nozzle
WO2015026417A2 (en) * 2013-05-31 2015-02-26 General Electric Company Dual-mode plug nozzle

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117685098A (en) * 2024-02-01 2024-03-12 西安航空学院 Stepless adjusting device for outer duct of variable-cycle engine
CN117685098B (en) * 2024-02-01 2024-04-05 西安航空学院 Stepless adjusting device for outer duct of variable-cycle engine

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