专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明专利

GB2400089A Aerofoil section 未知
公开(公告)号：GB2400089A
公开(公告)日：2004-10-06
申请号：GB0307804
申请日：2003-04-04
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： B64C3/14 , B64C11/18 , B64C27/467 , F04D29/38
摘要： An aerofoil has a leading edge 1, a trailing edge 3 and incorporates a step 2 along its chord. The aerofoil may be used in a turbofan, propeller, helicopter rotor blade or wing.

2. 发明专利

GB2354041B Variable mode jet engine-compact 未知
公开(公告)号：GB2354041B
公开(公告)日：2003-11-19
申请号：GB0016311
申请日：2000-07-04
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： F02K3/075 , F02K7/16
摘要： This jet engine comprises of a complete low bypass turbofan unit 1 including secondary fan unit 2 and engine core, some five to eight feet ahead of which sits a larger diameter main fan unit 3 driven from the turbofan 1 via drive shaft 4. Between the main and secondary fans sits a reversed variable area nozzle 5 connected to the forward end of the secondary fan by a short inlet tube 6, fitted with intercooler 12. At the back of said core sits another variable area nozzle 7 facing rearwards. This arrangement; front nozzle, inlet tube, secondary fan, core, rear nozzle, is enclosed by a variable diameter cylinder 8, providing a variable area bypass duct 9 between cylinder and engine outer casing 10 that extends backwards from the outer diameter of said main fan. A third variable area nozzle 11 is positioned aft of the outer casing facing rearwards.

3. 发明专利

GB2354041A Variable bypass jet engine 未知
公开(公告)号：GB2354041A
公开(公告)日：2001-03-14
申请号：GB0016311
申请日：2000-07-04
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： F02K3/075 , F02K7/16
摘要： The Jet engine comprises a low bypass turbofan unit, including a secondary fan (2 fig.C1) and core, some 1.5 to 2.5 metres ahead of which is located a larger diameter primary fan (3) driven from the front of the secondary fan, via drive shaft (4). Between the main and secondary fans is located a first variable-area nozzle (5), connected to the forward end of the secondary fan by a short tube (6) surrounded by an intercooler (12, fig. C3). To the rear of the core is located a second variable-area nozzle 7, facing rearwards. The first nozzle, tube, secondary fan, core and second nozzle are enclosed by a variable-diameter cylinder 8, thereby providing a variable-area bypass duct 9 between the cylinder and engine outer casing 10. A third variable-area nozzle 11 is positioned aft of the outer casing, facing rearwards. The first and second nozzles and cylinder may be completely expanded to close off the bypass duct altogether (fig. 1) whereupon all the air from the primary fan passes to the secondary fan.

4. 发明专利

GB2400089B High lift and high strength aerofoil section 未知
公开(公告)号：GB2400089B
公开(公告)日：2006-07-26
申请号：GB0307804
申请日：2003-04-04
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： B64C3/14 , B64C11/18 , B64C27/467 , F04D29/38

5. 发明专利

GB2400631B Compound centrifugal and screw compressor 未知
公开(公告)号：GB2400631B
公开(公告)日：2006-07-05
申请号：GB0308774
申请日：2003-04-16
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： F04D17/02 , F04D17/16 , F04D23/00 , F04D25/04 , F04D29/18
摘要： A compound centrifugal and screw compressor comprising two separate sections. The first section is a conventional centrifugal compressor body 2 with a plurality of radial vanes 3 and 4 on the front face. The second section of the compressor is a screw type compressor with a plurality of helical vanes 6 mounted on a conical screw body 5 ; the helical vanes 6 are lesser in number than the short radial vanes 4 and the same in number as the long radial vanes 3 , typically one quarter to one third, and mate up with longer radial vanes 3 at the extremity of the centrifugal 2 compressor rim. The conical screw body 5 is the same diameter as the outer rim of the centrifugal compressor and reduces down at the output end. The helical vanes each complete one full turn.

6. 发明专利

GB2400631A Compound compressor with centrifugal and helical screw stages 未知
公开(公告)号：GB2400631A
公开(公告)日：2004-10-20
申请号：GB0308774
申请日：2003-04-16
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： F04D17/16 , F04D25/04 , F04D17/02 , F04D23/00 , F04D29/18
摘要： A compound compressor, for a gas turbine engine, includes a centrifugal stage and helical screw stage. The centrifugal stage includes a body 2 with long vanes 3 and short vanes (4, figure 2), there being one quarter to one third the number of long vanes 3 compared to short vanes 4. The helical screw stage includes a conical body 5 with helical vanes 6. The body 5 of the helical screw mates with a rim of the centrifugal body 2, and the helical vanes 6 meet with the long vanes 3 of the centrifugal stage. The conical body 5 tapers towards a downstream end of the compressor, and each helical vane 6 completes one full turn. The compressor fits on to a shaft 1, and is housed within a casing 7. The compressor may be used in applications such as turbo shaft, turbo prop and turbo fan engines.

7. 发明专利

GB2353983B Variable mode jet engine-suitable for STOVL 未知
公开(公告)号：GB2353983B
公开(公告)日：2003-10-15
申请号：GB0016310
申请日：2000-07-04
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： B64C29/00 , F02K1/56 , F02K1/64 , F02K3/075 , F02K1/00 , B64C15/02
摘要： This jet engine comprises a complete low bypass turbofan unit 1 including secondary fan unit 2 and engine core, ahead of which sits a larger diameter main fan unit 3 driven from the front of the secondary fan via a long drive shaft 4. A center portion of the main fan feeds the secondary fan via long central duct 5. The outer portion of the main fan is ducted into a split exhaust plenum chamber 6. This chamber has thrust vectoring exhaust mechanisms 7 immediately attached to each side, and then each side then feeds a thrust splitter 10, and then feeds to variable area outer ducting 8, using double-hinged inner and outer doors 9. Both outer ducts rejoin the central duct downstream in a second plenum chamber 11 just ahead of the secondary fan. Between this chamber and secondary fan is an intercooler 12.

8. 发明专利

GB2353983A Variable mode turbofan jet engine with thrust vectoring 未知
公开(公告)号：GB2353983A
公开(公告)日：2001-03-14
申请号：GB0016310
申请日：2000-07-04
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： B64C29/00 , F02K1/56 , F02K1/64 , F02K3/075 , F02K1/00 , B64C15/02
摘要： The jet engine comprises a low bypass turbofan unit (1 fig. 1) including a secondary fan (2) and core, ahead of which is located a larger diameter main fan (3) driven from the front of the secondary fan, via drive shaft (4). Part of the flow from the main fan feeds the secondary fan, via a central duct (5). The outer Portion of the airflow from the main fan is ducted into a split exhaust plenum chamber 6, having thrust-vectoring devices 7. A thrust splitter 10, is provided at each forward end of two variable-area outer ducts 8, defined by double-hinged inner and outer doors 9, whereby the degree of bypass and supercharging of the secondary compressor by air from the main fan can be varied. Both outer ducts join at a point 11, just ahead of the secondary fan. Between this joint and the secondary fan an intercooler (12, fig. S3) may be provided.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式