| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | Mule spinning machine | US37615641 | 1941-01-27 | US2281969A | 1942-05-05 | GARD ROBERT A |
| 2 | Automatic bunch builder | US23956538 | 1938-11-08 | US2204786A | 1940-06-18 | GEORGE BICKFORD |
| 3 | Regulator for winding on installations | US46657030 | 1930-07-08 | US1903588A | 1933-04-11 | JOSEPH DETHIER |
| 4 | Gas turbine engine | EP11178577.0 | 2011-08-24 | EP2428648A2 | 2012-03-14 | King, Jonathan Michael; Bolgar, Crispin David; Snowsill, Guy David |
A gas turbine engine has a compressor section with rotational compressor components rotatable with respect to static compressor components. A compressed air bleed arrangement is provided to cool one or more other rotational components of the gas turbine engine. The compressed air bleed arrangement takes a flow of compressed air from the compressor section along an off-take passage. The off-take passage opens in the compressor section at an off-take port. The off-take passage is rotatable, in use, with the rotational compressor components. The compressed air bleed arrangement is operable to provide the air in the off-take passage with higher static pressure than the air in the compressor section at the off-take port, by diffusing the air in the off-take passage. The off-take passage further includes off-take vanes, operable to increase the tangential velocity of the air in the off-take passage compared with the air at the off-take port.
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| 5 | Gas turbine engine | EP11178577.0 | 2011-08-24 | EP2428648B1 | 2016-10-05 | King, Jonathan Michael; Bolgar, Crispin David; Snowsill, Guy David |
| 6 | Gas turbine engine | EP11178577.0 | 2011-08-24 | EP2428648A3 | 2014-01-22 | King, Jonathan Michael; Bolgar, Crispin David; Snowsill, Guy David |
A gas turbine engine has a compressor section with rotational compressor components rotatable with respect to static compressor components. A compressed air bleed arrangement is provided to cool one or more other rotational components of the gas turbine engine. The compressed air bleed arrangement takes a flow of compressed air from the compressor section along an off-take passage. The off-take passage opens in the compressor section at an off-take port. The off-take passage is rotatable, in use, with the rotational compressor components. The compressed air bleed arrangement is operable to provide the air in the off-take passage with higher static pressure than the air in the compressor section at the off-take port, by diffusing the air in the off-take passage. The off-take passage further includes off-take vanes, operable to increase the tangential velocity of the air in the off-take passage compared with the air at the off-take port.
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| 7 | Gas turbine engine havinga rotatable off-take passage in a compressor section | US13216691 | 2011-08-24 | US09103281B2 | 2015-08-11 | Jonathan M King; Crispin D Bolgar; Guy D Snowsill |
| A gas turbine engine has a compressor section with rotational compressor components rotatable with respect to static compressor components. A compressed air bleed arrangement is provided to cool one or more other rotational components of the gas turbine engine. The compressed air bleed arrangement takes a flow of compressed air from the compressor section along an off-take passage. The off-take passage opens in the compressor section at an off-take port. The off-take passage is rotatable, in use, with the rotational compressor components. The compressed air bleed arrangement is operable to provide the air in the off-take passage with higher static pressure than the air in the compressor section at the off-take port, by diffusing the air in the off-take passage. The off-take passage further includes off-take vanes, operable to increase the tangential velocity of the air in the off-take passage compared with the air at the off-take port. | ||||||
| 8 | GAS TURBINE ENGINE | US13216691 | 2011-08-24 | US20120060506A1 | 2012-03-15 | Jonathan M. KING; Crispin D. BOLGAR; Guy D. SNOWSILL |
| A gas turbine engine has a compressor section with rotational compressor components rotatable with respect to static compressor components. A compressed air bleed arrangement is provided to cool one or more other rotational components of the gas turbine engine. The compressed air bleed arrangement takes a flow of compressed air from the compressor section along an off-take passage. The off-take passage opens in the compressor section at an off-take port. The off-take passage is rotatable, in use, with the rotational compressor components. The compressed air bleed arrangement is operable to provide the air in the off-take passage with higher static pressure than the air in the compressor section at the off-take port, by diffusing the air in the off-take passage. The off-take passage further includes off-take vanes, operable to increase the tangential velocity of the air in the off-take passage compared with the air at the off-take port. | ||||||
| 9 | Spinning mule | US34793853 | 1953-04-10 | US2883823A | 1959-04-28 | AUGUST KRAUSE |
| 10 | Mule spinning device | US69468746 | 1946-09-04 | US2442725A | 1948-06-01 | GARD ROBERT A |
| 11 | Mule spinning device | US64783646 | 1946-02-15 | US2442724A | 1948-06-01 | GARD ROBERT A |
| 12 | Faller arm for spinning mules | US59878245 | 1945-06-11 | US2416627A | 1947-02-25 | JOHNSON JOHN C |
| 13 | Mule spinning device | US21398138 | 1938-06-16 | US2219685A | 1940-10-29 | GARD ROBERT A |
| 14 | Bunch builder for spinning mules | US17158337 | 1937-10-28 | US2125196A | 1938-07-26 | PAOLUCEI CARL J |
| 15 | Tension faller bar for spinning mules | US42279330 | 1930-01-23 | US1811352A | 1931-06-23 | FEUGILL WALTER A; HOSKING JOHN R |
| 16 | Means for producing cross-wound cops in spinning mules and the like | US18225627 | 1927-04-09 | US1672024A | 1928-06-05 | STAFFORD GOLLAND HENRY |
| 17 | Rail gauge for spinning frames | US61237123 | 1923-01-13 | US1531652A | 1925-03-31 | GUILLET ALBERT M |
