GB2426792B - A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan (or fans) of an aero-engine system - Google Patents

A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan (or fans) of an aero-engine system

Info

Publication number
GB2426792B
GB2426792B GB0515496A GB0515496A GB2426792B GB 2426792 B GB2426792 B GB 2426792B GB 0515496 A GB0515496 A GB 0515496A GB 0515496 A GB0515496 A GB 0515496A GB 2426792 B GB2426792 B GB 2426792B
Authority
GB
United Kingdom
Prior art keywords
aero
fans
throughput
fluid
design
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.)
Active
Application number
GB0515496A
Other versions
GB2426792C (en
GB0515496D0 (en
GB2426792A9 (en
GB2426792A (en
Inventor
David Richard Hopkins
Original Assignee
David Richard Hopkins
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 to GBGB0506685.7A priority Critical patent/GB0506685D0/en
Application filed by David Richard Hopkins filed Critical David Richard Hopkins
Publication of GB0515496D0 publication Critical patent/GB0515496D0/en
Publication of GB2426792A publication Critical patent/GB2426792A/en
Publication of GB2426792A9 publication Critical patent/GB2426792A9/en
Publication of GB2426792B publication Critical patent/GB2426792B/en
Application granted granted Critical
Publication of GB2426792C publication Critical patent/GB2426792C/en
Application status is Active legal-status Critical
Anticipated expiration legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K3/00Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02Plants 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
    • F02K3/04Plants 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
    • F02K3/075Plants 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 controlling flow ratio between flows
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K3/00Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02Plants 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
    • F02K3/04Plants 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
    • F02K3/06Plants 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00Axial-flow pumps
    • F04D19/002Axial flow fans
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/26Rotors specially for elastic fluids
    • F04D29/32Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/26Rotors specially for elastic fluids
    • F04D29/32Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/329Details of the hub
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/26Rotors specially for elastic fluids
    • F04D29/32Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38Blades
    • F04D29/384Blades characterised by form
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/52Casings; Connections of working fluid for axial pumps
    • F04D29/54Fluid-guiding means, e.g. diffusers
    • F04D29/541Specially adapted for elastic fluid pumps
    • F04D29/545Ducts
    • F04D29/547Ducts having a special shape in order to influence fluid flow
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies
    • Y02T50/67Relevant aircraft propulsion technologies
    • Y02T50/671Measures to reduce the propulsor weight
GB0515496A 2005-04-01 2005-07-28 A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan(or fans) of an aero-engine system Active GB2426792C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GBGB0506685.7A GB0506685D0 (en) 2005-04-01 2005-04-01 A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan (or fans) of an aero-engine system

Publications (5)

Publication Number Publication Date
GB0515496D0 GB0515496D0 (en) 2005-09-07
GB2426792A GB2426792A (en) 2006-12-06
GB2426792A9 GB2426792A9 (en) 2007-05-23
GB2426792B true GB2426792B (en) 2007-06-27
GB2426792C GB2426792C (en) 2008-03-06

Family

ID=34586579

Family Applications (2)

Application Number Title Priority Date Filing Date
GBGB0506685.7A Ceased GB0506685D0 (en) 2005-04-01 2005-04-01 A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan (or fans) of an aero-engine system
GB0515496A Active GB2426792C (en) 2005-04-01 2005-07-28 A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan(or fans) of an aero-engine system

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GBGB0506685.7A Ceased GB0506685D0 (en) 2005-04-01 2005-04-01 A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan (or fans) of an aero-engine system

Country Status (1)

Country Link
GB (2) GB0506685D0 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9840969B2 (en) 2012-05-31 2017-12-12 United Technologies Corporation Gear system architecture for gas turbine engine
US10527151B1 (en) 2006-08-15 2020-01-07 United Technologies Corporation Gas turbine engine with geared architecture
US10577965B2 (en) 2006-08-15 2020-03-03 United Technologies Corporation Epicyclic gear train
US10591047B2 (en) 2018-10-22 2020-03-17 United Technologies Corporation Ring gear mounting arrangement with oil scavenge scheme

Families Citing this family (27)

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US8858388B2 (en) 2006-08-15 2014-10-14 United Technologies Corporation Gas turbine engine gear train
US8753243B2 (en) 2006-08-15 2014-06-17 United Technologies Corporation Ring gear mounting arrangement with oil scavenge scheme
US20080273961A1 (en) 2007-03-05 2008-11-06 Rosenkrans William E Flutter sensing and control system for a gas turbine engine
US20150377123A1 (en) 2007-08-01 2015-12-31 United Technologies Corporation Turbine section of high bypass turbofan
US9701415B2 (en) 2007-08-23 2017-07-11 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US20140174056A1 (en) 2008-06-02 2014-06-26 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US9239012B2 (en) 2011-06-08 2016-01-19 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US9506422B2 (en) 2011-07-05 2016-11-29 United Technologies Corporation Efficient, low pressure ratio propulsor for gas turbine engines
US9909505B2 (en) 2011-07-05 2018-03-06 United Technologies Corporation Efficient, low pressure ratio propulsor for gas turbine engines
US9416677B2 (en) 2012-01-10 2016-08-16 United Technologies Corporation Gas turbine engine forward bearing compartment architecture
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US20150345426A1 (en) 2012-01-31 2015-12-03 United Technologies Corporation Geared turbofan gas turbine engine architecture
US8935913B2 (en) 2012-01-31 2015-01-20 United Technologies Corporation Geared turbofan gas turbine engine architecture
US9835052B2 (en) 2012-01-31 2017-12-05 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US8790075B2 (en) 2012-03-30 2014-07-29 United Technologies Corporation Gas turbine engine geared architecture axial retention arrangement
US9169731B2 (en) 2012-06-05 2015-10-27 United Technologies Corporation Airfoil cover system
US9920653B2 (en) 2012-12-20 2018-03-20 United Technologies Corporation Low pressure ratio fan engine having a dimensional relationship between inlet and fan size
CN103062113A (en) * 2013-01-23 2013-04-24 薛文义 Fan mechanism of turbo-fan engine
US20160215729A1 (en) 2013-03-15 2016-07-28 United Technologies Corporation Thrust efficient turbofan engine
WO2014151785A1 (en) 2013-03-15 2014-09-25 United Technologies Corporation Turbofan engine bearing and gearbox arrangement
US10371047B2 (en) 2013-10-16 2019-08-06 United Technologies Corporation Geared turbofan engine with targeted modular efficiency
WO2015126449A1 (en) 2014-02-19 2015-08-27 United Technologies Corporation Gas turbine engine airfoil
US9599064B2 (en) 2014-02-19 2017-03-21 United Technologies Corporation Gas turbine engine airfoil
WO2015126454A1 (en) 2014-02-19 2015-08-27 United Technologies Corporation Gas turbine engine airfoil
US9879608B2 (en) 2014-03-17 2018-01-30 United Technologies Corporation Oil loss protection for a fan drive gear system
US9470093B2 (en) 2015-03-18 2016-10-18 United Technologies Corporation Turbofan arrangement with blade channel variations
US10233773B2 (en) 2015-11-17 2019-03-19 United Technologies Corporation Monitoring system for non-ferrous metal particles

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1070333B (en) *
GB981188A (en) * 1960-12-19 1965-01-20 Lyonnaise Ventilation Improved helicoidal fan
GB1033502A (en) * 1962-02-15 1966-06-22 Gen Dynamics Corp Mixed flow blowers
US3508842A (en) * 1968-10-08 1970-04-28 Trane Co Apparatus for improving axial velocity profile of axial flow fans
US3914068A (en) * 1972-01-25 1975-10-21 Sueddeutsche Kuehler Behr Fan for motor vehicles
GB1482933A (en) * 1973-10-23 1977-08-17 Onera (Off Nat Aerospatiale) Supersonic flow compressors
US4063852A (en) * 1976-01-28 1977-12-20 Torin Corporation Axial flow impeller with improved blade shape
US4678410A (en) * 1984-08-03 1987-07-07 Braun Aktiengesellschaft Hair dryer with axial blower
EP0675290A2 (en) * 1994-03-28 1995-10-04 Research Institute Of Advanced Material Gas-Generator, Ltd. Axial flow compressor
WO2000003136A1 (en) * 1998-07-09 2000-01-20 Pratt & Whitney Canada Corp. Integrated fan/low pressure compressor rotor for gas turbine engine
US6195983B1 (en) * 1999-02-12 2001-03-06 General Electric Company Leaned and swept fan outlet guide vanes
EP1126133A2 (en) * 2000-02-18 2001-08-22 General Electric Company Convex compressor casing
GB2363170A (en) * 2000-06-08 2001-12-12 Rolls Royce Plc Attaching a nose cone to a gas turbine engine rotor
GB2398353A (en) * 2003-02-14 2004-08-18 Rolls Royce Plc A gas turbine engine nose cone

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1070333B (en) *
GB981188A (en) * 1960-12-19 1965-01-20 Lyonnaise Ventilation Improved helicoidal fan
GB1033502A (en) * 1962-02-15 1966-06-22 Gen Dynamics Corp Mixed flow blowers
US3508842A (en) * 1968-10-08 1970-04-28 Trane Co Apparatus for improving axial velocity profile of axial flow fans
US3914068A (en) * 1972-01-25 1975-10-21 Sueddeutsche Kuehler Behr Fan for motor vehicles
GB1482933A (en) * 1973-10-23 1977-08-17 Onera (Off Nat Aerospatiale) Supersonic flow compressors
US4063852A (en) * 1976-01-28 1977-12-20 Torin Corporation Axial flow impeller with improved blade shape
US4678410A (en) * 1984-08-03 1987-07-07 Braun Aktiengesellschaft Hair dryer with axial blower
EP0675290A2 (en) * 1994-03-28 1995-10-04 Research Institute Of Advanced Material Gas-Generator, Ltd. Axial flow compressor
WO2000003136A1 (en) * 1998-07-09 2000-01-20 Pratt & Whitney Canada Corp. Integrated fan/low pressure compressor rotor for gas turbine engine
US6195983B1 (en) * 1999-02-12 2001-03-06 General Electric Company Leaned and swept fan outlet guide vanes
EP1126133A2 (en) * 2000-02-18 2001-08-22 General Electric Company Convex compressor casing
GB2363170A (en) * 2000-06-08 2001-12-12 Rolls Royce Plc Attaching a nose cone to a gas turbine engine rotor
GB2398353A (en) * 2003-02-14 2004-08-18 Rolls Royce Plc A gas turbine engine nose cone

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10527151B1 (en) 2006-08-15 2020-01-07 United Technologies Corporation Gas turbine engine with geared architecture
US10570855B2 (en) 2006-08-15 2020-02-25 United Technologies Corporation Gas turbine engine with geared architecture
US10577965B2 (en) 2006-08-15 2020-03-03 United Technologies Corporation Epicyclic gear train
US9840969B2 (en) 2012-05-31 2017-12-12 United Technologies Corporation Gear system architecture for gas turbine engine
US10590802B2 (en) 2018-09-07 2020-03-17 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US10591047B2 (en) 2018-10-22 2020-03-17 United Technologies Corporation Ring gear mounting arrangement with oil scavenge scheme

Also Published As

Publication number Publication date
GB0515496D0 (en) 2005-09-07
GB0506685D0 (en) 2005-05-11
GB2426792A9 (en) 2007-05-23
GB2426792A (en) 2006-12-06
GB2426792C (en) 2008-03-06

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