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 systemInfo
- 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.)
- Expired - Fee Related
Links
Classifications
-
- 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
- F02K3/075—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 controlling flow ratio between flows
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
- F04D19/002—Axial flow fans
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
- F04D29/329—Details of the hub
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/545—Ducts
- F04D29/547—Ducts having a special shape in order to influence fluid flow
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (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 Expired - Fee Related 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 (2)
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 |
US10830152B2 (en) | 2007-09-21 | 2020-11-10 | Raytheon Technologies Corporation | Gas turbine engine compressor arrangement |
Families Citing this family (98)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7704178B2 (en) | 2006-07-05 | 2010-04-27 | United Technologies Corporation | Oil baffle for gas turbine fan drive gear system |
US8667688B2 (en) | 2006-07-05 | 2014-03-11 | United Technologies Corporation | Method of assembly for gas turbine fan drive gear system |
US8753243B2 (en) | 2006-08-15 | 2014-06-17 | United Technologies Corporation | Ring gear mounting arrangement with oil scavenge scheme |
US10107231B2 (en) | 2006-08-15 | 2018-10-23 | United Technologies Corporation | Gas turbine engine with geared architecture |
US9976437B2 (en) | 2006-08-15 | 2018-05-22 | United Technologies Corporation | Epicyclic gear train |
US8858388B2 (en) | 2006-08-15 | 2014-10-14 | United Technologies Corporation | Gas turbine engine gear train |
WO2008045072A1 (en) | 2006-10-12 | 2008-04-17 | United Technologies Corporation | Dual function cascade integrated variable area fan nozzle and thrust reverser |
US20080273961A1 (en) | 2007-03-05 | 2008-11-06 | Rosenkrans William E | Flutter sensing and control system for a gas turbine engine |
US11486311B2 (en) | 2007-08-01 | 2022-11-01 | Raytheon Technologies Corporation | Turbine section of high bypass turbofan |
US11346289B2 (en) | 2007-08-01 | 2022-05-31 | Raytheon Technologies Corporation | Turbine section of high bypass turbofan |
US11242805B2 (en) | 2007-08-01 | 2022-02-08 | Raytheon Technologies Corporation | Turbine section of high bypass turbofan |
US11149650B2 (en) | 2007-08-01 | 2021-10-19 | Raytheon Technologies Corporation | Turbine section of high bypass turbofan |
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 |
US9957918B2 (en) | 2007-08-28 | 2018-05-01 | United Technologies Corporation | Gas turbine engine front architecture |
US20140174056A1 (en) | 2008-06-02 | 2014-06-26 | United Technologies Corporation | Gas turbine engine with low stage count low pressure turbine |
US9885313B2 (en) | 2009-03-17 | 2018-02-06 | United Technologes Corporation | Gas turbine engine bifurcation located fan variable area nozzle |
US9995174B2 (en) | 2010-10-12 | 2018-06-12 | United Technologies Corporation | Planetary gear system arrangement with auxiliary oil system |
US10605167B2 (en) | 2011-04-15 | 2020-03-31 | United Technologies Corporation | Gas turbine engine front center body architecture |
US9523422B2 (en) | 2011-06-08 | 2016-12-20 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US9239012B2 (en) | 2011-06-08 | 2016-01-19 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US9631558B2 (en) | 2012-01-03 | 2017-04-25 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
US9909505B2 (en) | 2011-07-05 | 2018-03-06 | United Technologies Corporation | Efficient, low pressure ratio propulsor for gas turbine engines |
US9506422B2 (en) | 2011-07-05 | 2016-11-29 | United Technologies Corporation | Efficient, low pressure ratio propulsor for gas turbine engines |
US9938898B2 (en) | 2011-07-29 | 2018-04-10 | United Technologies Corporation | Geared turbofan bearing arrangement |
US9416677B2 (en) | 2012-01-10 | 2016-08-16 | United Technologies Corporation | Gas turbine engine forward bearing compartment architecture |
US20130186058A1 (en) | 2012-01-24 | 2013-07-25 | William G. Sheridan | Geared turbomachine fan and compressor rotation |
US20150345426A1 (en) | 2012-01-31 | 2015-12-03 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US10724431B2 (en) | 2012-01-31 | 2020-07-28 | Raytheon Technologies Corporation | Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine |
US10113434B2 (en) | 2012-01-31 | 2018-10-30 | United Technologies Corporation | Turbine blade damper seal |
US8869508B2 (en) | 2012-01-31 | 2014-10-28 | United Technologies Corporation | Gas turbine engine variable area fan nozzle control |
US20130192251A1 (en) | 2012-01-31 | 2013-08-01 | Peter M. Munsell | Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine |
US9394852B2 (en) | 2012-01-31 | 2016-07-19 | United Technologies Corporation | Variable area fan nozzle with wall thickness distribution |
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 |
US8863491B2 (en) | 2012-01-31 | 2014-10-21 | United Technologies Corporation | Gas turbine engine shaft bearing configuration |
US20130192240A1 (en) | 2012-01-31 | 2013-08-01 | Peter M. Munsell | Buffer system for a gas turbine engine |
US20130192191A1 (en) | 2012-01-31 | 2013-08-01 | Frederick M. Schwarz | Gas turbine engine with high speed low pressure turbine section and bearing support features |
US9169781B2 (en) | 2012-01-31 | 2015-10-27 | United Technologies Corporation | Turbine engine gearbox |
US8935913B2 (en) | 2012-01-31 | 2015-01-20 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US20150192070A1 (en) | 2012-01-31 | 2015-07-09 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US20130192198A1 (en) | 2012-01-31 | 2013-08-01 | Lisa I. Brilliant | Compressor flowpath |
US10415468B2 (en) | 2012-01-31 | 2019-09-17 | United Technologies Corporation | Gas turbine engine buffer system |
US10400629B2 (en) | 2012-01-31 | 2019-09-03 | United Technologies Corporation | Gas turbine engine shaft bearing configuration |
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 |
US10107191B2 (en) | 2012-02-29 | 2018-10-23 | United Technologies Corporation | Geared gas turbine engine with reduced fan noise |
US8790075B2 (en) | 2012-03-30 | 2014-07-29 | United Technologies Corporation | Gas turbine engine geared architecture axial retention arrangement |
US10138809B2 (en) | 2012-04-02 | 2018-11-27 | United Technologies Corporation | Geared turbofan engine with a high ratio of thrust to turbine volume |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US8572943B1 (en) | 2012-05-31 | 2013-11-05 | United Technologies Corporation | Fundamental gear system architecture |
US9169731B2 (en) | 2012-06-05 | 2015-10-27 | United Technologies Corporation | Airfoil cover system |
US9863319B2 (en) | 2012-09-28 | 2018-01-09 | United Technologies Corporation | Split-zone flow metering T-tube |
WO2014058453A1 (en) | 2012-10-08 | 2014-04-17 | United Technologies Corporation | Geared turbine engine with relatively lightweight propulsor module |
EP2909460A4 (en) | 2012-10-09 | 2016-07-20 | United Technologies Corp | Improved operability geared turbofan engine including compressor section variable guide vanes |
US9932933B2 (en) | 2012-12-20 | 2018-04-03 | United Technologies Corporation | Low pressure ratio fan engine having a dimensional relationship between inlet and fan size |
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 |
US10436120B2 (en) | 2013-02-06 | 2019-10-08 | United Technologies Corporation | Exhaust nozzle for an elongated gear turbofan with high bypass ratio |
EP3882448A1 (en) | 2013-03-12 | 2021-09-22 | Raytheon Technologies Corporation | Flexible coupling for geared turbine engine |
US10605172B2 (en) | 2013-03-14 | 2020-03-31 | United Technologies Corporation | Low noise turbine for geared gas turbine engine |
US11719161B2 (en) | 2013-03-14 | 2023-08-08 | Raytheon Technologies Corporation | Low noise turbine for geared gas turbine engine |
WO2014151785A1 (en) | 2013-03-15 | 2014-09-25 | United Technologies Corporation | Turbofan engine bearing and gearbox arrangement |
US10724479B2 (en) | 2013-03-15 | 2020-07-28 | United Technologies Corporation | Thrust efficient turbofan engine |
US10287917B2 (en) | 2013-05-09 | 2019-05-14 | United Technologies Corporation | Turbofan engine front section |
EP3058202A4 (en) | 2013-10-16 | 2017-06-28 | United Technologies Corporation | Geared turbofan engine with targeted modular efficiency |
WO2015112212A2 (en) | 2013-11-01 | 2015-07-30 | United Technologies Corporation | Geared turbofan arrangement with core split power ratio |
US10502163B2 (en) | 2013-11-01 | 2019-12-10 | United Technologies Corporation | Geared turbofan arrangement with core split power ratio |
US8869504B1 (en) | 2013-11-22 | 2014-10-28 | United Technologies Corporation | Geared turbofan engine gearbox arrangement |
EP3108104B1 (en) | 2014-02-19 | 2019-06-12 | United Technologies Corporation | Gas turbine engine airfoil |
US10570915B2 (en) | 2014-02-19 | 2020-02-25 | United Technologies Corporation | Gas turbine engine airfoil |
WO2015175073A2 (en) | 2014-02-19 | 2015-11-19 | United Technologies Corporation | Gas turbine engine airfoil |
WO2015175052A2 (en) | 2014-02-19 | 2015-11-19 | United Technologies Corporation | Gas turbine engine airfoil |
WO2015126715A1 (en) | 2014-02-19 | 2015-08-27 | United Technologies Corporation | Gas turbine engine airfoil |
EP3108120B1 (en) | 2014-02-19 | 2021-03-31 | Raytheon Technologies Corporation | Gas turbine engine having a geared architecture and a specific fixed airfoil structure |
US10570916B2 (en) | 2014-02-19 | 2020-02-25 | United Technologies Corporation | Gas turbine engine airfoil |
WO2015126449A1 (en) | 2014-02-19 | 2015-08-27 | United Technologies Corporation | Gas turbine engine airfoil |
US10495106B2 (en) | 2014-02-19 | 2019-12-03 | United Technologies Corporation | Gas turbine engine airfoil |
EP3108119B1 (en) | 2014-02-19 | 2023-10-04 | RTX Corporation | Turbofan engine with geared architecture and lpc blade airfoils |
US10465702B2 (en) | 2014-02-19 | 2019-11-05 | United Technologies Corporation | Gas turbine engine airfoil |
US10280843B2 (en) | 2014-03-07 | 2019-05-07 | United Technologies Corporation | Geared turbofan with integral front support and carrier |
US9879608B2 (en) | 2014-03-17 | 2018-01-30 | United Technologies Corporation | Oil loss protection for a fan drive gear system |
US9976490B2 (en) | 2014-07-01 | 2018-05-22 | United Technologies Corporation | Geared gas turbine engine with oil deaerator |
US10060289B2 (en) | 2014-07-29 | 2018-08-28 | United Technologies Corporation | Geared gas turbine engine with oil deaerator and air removal |
US9915225B2 (en) | 2015-02-06 | 2018-03-13 | United Technologies Corporation | Propulsion system arrangement for turbofan gas turbine engine |
US9470093B2 (en) | 2015-03-18 | 2016-10-18 | United Technologies Corporation | Turbofan arrangement with blade channel variations |
US10371168B2 (en) | 2015-04-07 | 2019-08-06 | United Technologies Corporation | Modal noise reduction for gas turbine engine |
US9874145B2 (en) | 2015-04-27 | 2018-01-23 | United Technologies Corporation | Lubrication system for gas turbine engines |
US10458270B2 (en) | 2015-06-23 | 2019-10-29 | United Technologies Corporation | Roller bearings for high ratio geared turbofan engine |
US10233773B2 (en) | 2015-11-17 | 2019-03-19 | United Technologies Corporation | Monitoring system for non-ferrous metal particles |
US10508562B2 (en) | 2015-12-01 | 2019-12-17 | United Technologies Corporation | Geared turbofan with four star/planetary gear reduction |
US10669948B2 (en) | 2017-01-03 | 2020-06-02 | Raytheon Technologies Corporation | Geared turbofan with non-epicyclic gear reduction system |
RU2756944C2 (en) * | 2017-02-23 | 2021-10-07 | Майнтек Инвестментс Пти Лтд | Fan improvements |
US10738646B2 (en) | 2017-06-12 | 2020-08-11 | Raytheon Technologies Corporation | Geared turbine engine with gear driving low pressure compressor and fan at common speed, and failsafe overspeed protection and shear section |
US10724445B2 (en) | 2018-01-03 | 2020-07-28 | Raytheon Technologies Corporation | Method of assembly for fan drive gear system with rotating carrier |
US11092020B2 (en) | 2018-10-18 | 2021-08-17 | Raytheon Technologies Corporation | Rotor assembly for gas turbine engines |
US11781506B2 (en) | 2020-06-03 | 2023-10-10 | Rtx Corporation | Splitter and guide vane arrangement for gas turbine engines |
US11719245B2 (en) | 2021-07-19 | 2023-08-08 | Raytheon Technologies Corporation | Compressor arrangement for a gas turbine engine |
US11754000B2 (en) | 2021-07-19 | 2023-09-12 | Rtx Corporation | High and low spool configuration for a gas turbine engine |
US11814968B2 (en) | 2021-07-19 | 2023-11-14 | Rtx Corporation | Gas turbine engine with idle thrust ratio |
Citations (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1070333B (en) * | 1959-12-31 | |||
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 |
-
2005
- 2005-04-01 GB GBGB0506685.7A patent/GB0506685D0/en not_active Ceased
- 2005-07-28 GB GB0515496A patent/GB2426792C/en not_active Expired - Fee Related
Patent Citations (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1070333B (en) * | 1959-12-31 | |||
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 (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10830152B2 (en) | 2007-09-21 | 2020-11-10 | Raytheon Technologies Corporation | Gas turbine engine compressor arrangement |
US11846238B2 (en) | 2007-09-21 | 2023-12-19 | Rtx Corporation | Gas turbine engine compressor arrangement |
US9840969B2 (en) | 2012-05-31 | 2017-12-12 | United Technologies Corporation | Gear system architecture for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
GB2426792A9 (en) | 2007-05-23 |
GB0515496D0 (en) | 2005-09-07 |
GB2426792C (en) | 2008-03-06 |
GB0506685D0 (en) | 2005-05-11 |
GB2426792A (en) | 2006-12-06 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB2426792C (en) | 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 | |
EP1933040A4 (en) | Turbo fan and air conditioner | |
TW200720554A (en) | Fan and fan housing with toothed-type connecting elements | |
GB2442422B8 (en) | Gas turbine exhaust diffuser | |
NO20090546L (en) | Improved engine with active expansion chamber for compressed air or gas and / or additional energy. | |
EP2541020A3 (en) | System for ventilating a gas turbine enclosure | |
MX2010002496A (en) | A fan. | |
GB2433586B (en) | A fan coil air conditioning system and inlet therefor | |
WO2008048248A3 (en) | Building protection system and method | |
WO2013074483A3 (en) | Ventilating system and method | |
DE60302216D1 (en) | outlet assembly | |
EP1733127A4 (en) | Gas turbine inlet flow straightener with restricting member | |
IL173839A0 (en) | Gas turbine engine air valve assembly | |
TW200639327A (en) | Heat-dissipating device and frame thereof | |
TWI263735B (en) | Heat-dissipating device | |
EP2059679A4 (en) | Oil-free air compressor system with inlet throttle | |
DE602007000645D1 (en) | Rectifier for axial fans, in particular for air conditioning systems | |
TW200622111A (en) | Fan duct device | |
ATE542172T1 (en) | FAN UNIT | |
ATE548609T1 (en) | COOKING APPLIANCE | |
TW200702558A (en) | Blower | |
WO2009092546A3 (en) | Kitchen exhaust ultraviolet system | |
WO2008111098A8 (en) | Air intake for a gas turbine compressor | |
TW200736508A (en) | Serial fan assembly and air-guiding structure thereof | |
FR2931348B1 (en) | COOKING DEVICE |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20200728 |