公开(公告)号：WO2015122948A3

公开(公告)日：2015-10-15

申请号：PCT/US2014066273

申请日：2014-11-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W

IPC: F02C7/12 ,  F02C7/18

CPC classification number: F02C7/143 ,  F02C3/107 ,  F02C7/08 ,  F02C7/10 ,  F02C7/185 ,  F02K3/077 ,  F05D2220/32 ,  F05D2250/30 ,  F05D2250/311 ,  F05D2260/211 ,  Y02T50/675

Abstract: A gas turbine engine includes a first stage compressor, an intercooler in fluid communication with the first stage compressor, and a second stage compressor in fluid communication with the intercooler. The engine also includes a combustor in fluid communication with the second stage compressor and a turbine in fluid communication with the combustor. The intercooler cools an air inflow from the first stage compressor and the recuperator heats the airflow traveling from the second stage compressor to the turbine exhaust. The intercooler and recuperator are arranged radially outward of the combustor.

Abstract translation: 燃气涡轮发动机包括第一级压缩机，与第一级压缩机流体连通的中间冷却器以及与中间冷却器流体连通的第二级压缩机。 发动机还包括与第二级压缩机流体连通的燃烧器和与燃烧器流体连通的涡轮机。 中间冷却器冷却来自第一级压缩机的空气流入，并且回流换热器加热从第二级压缩机行进到涡轮机废气的气流。 中间冷却器和换热器布置在燃烧器的径向外侧。

公开(公告)号：DE602005000796T2

公开(公告)日：2007-08-16

申请号：DE602005000796

申请日：2005-05-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W ,  KRAUSE DAVID ,  GREGG SHAWN J ,  CUCINELLA FRANK THOMAS ,  SURACE RAYMOND C ,  MONGILLO JR DOMINIC J

IPC: F01D5/18 ,  F02C7/18

Abstract: A rotor blade (14) is provided having a hollow airfoil (72) and a root (20). The hollow airfoil (22) has a cavity (40) and one or more cooling apertures (32,76,90). The root (20) is attached to the airfoil (22), and has a leading edge conduit (42), at least one mid-body conduit (44), and a trailing edge conduit (46). The conduits are operable to permit airflow through the root and into the cavity. Each conduit (42,44,46) has a centerline (58,74,88). The leading edge conduit (42) includes an inlet (48) having a forward side (50), a suction side (52), and a pressure side (56) that diverge from the centerline (58) of the leading edge conduit (42), and an aft side (52). Each of the mid-body conduits (44) includes an inlet (64) having a suction side (66) and a pressure side (68) that diverge from the centerline (74) of the mid-body conduit (44), and an aft side (70) and a forward side (72). The trailing edge conduit (46) includes an inlet (78) having a suction side (84) and a pressure side (86) that diverge from the centerline (88) of the trailing edge conduit (46). The trailing edge conduit inlet (78) further includes a forward side (82) and an aft side (80).

公开(公告)号：CA2879756C

公开(公告)日：2017-04-11

申请号：CA2879756

申请日：2013-07-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W

IPC: F02C3/00 ,  F02C7/00

Abstract: A gas turbine engine comprises a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case, a shaft rotatable relative to the fan case about an engine center axis, and a geared architecture driven by the shaft to provide driving output to rotate the fan hub. A compressor is positioned forward of the geared architecture and radially inward of the fan blades, with the compressor being driven by the shaft.

公开(公告)号：DE708875T1

公开(公告)日：1996-10-24

申请号：DE94902283

申请日：1993-11-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W

IPC: F01D5/18 ,  F02K3/06

Abstract: A rotor blade having an integral platform with a cooled fillet is disclosed. Various construction details are developed which provide a cooling hole extending in proximity of the fillet to convectively cool the fillet. In a particular embodiment, a rotor blade having a integral platform and fillet includes a cooling hole extending between an internal cooling passage and a damper cavity. The cooling hole has a streamwise axis oriented in the direction to a line tangent to a midpoint of the fillet. The cooling hole directs a flow of cooling fluid radially inward and laterally outward, the cooling fluid flowing in proximity to the fillet to provide convective cooling.

公开(公告)号：CA2879756A1

公开(公告)日：2014-01-30

申请号：CA2879756

申请日：2013-07-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W

IPC: F02C3/00 ,  F02C7/00

Abstract: A gas turbine engine comprises a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case, a shaft rotatable relative to the fan case about an engine center axis, and a geared architecture driven by the shaft to provide driving output to rotate the fan hub. A compressor is positioned forward of the geared architecture and radially inward of the fan blades, with the compressor being driven by the shaft.

公开(公告)号：DE602005000796D1

公开(公告)日：2007-05-16

申请号：DE602005000796

申请日：2005-05-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W ,  KRAUSE DAVID ,  GREGG SHAWN J ,  CUCINELLA FRANK THOMAS ,  SURACE RAYMOND C ,  MONGILLO JR DOMINIC J

IPC: F01D5/18 ,  F02C7/18

Abstract: A rotor blade (14) is provided having a hollow airfoil (72) and a root (20). The hollow airfoil (22) has a cavity (40) and one or more cooling apertures (32,76,90). The root (20) is attached to the airfoil (22), and has a leading edge conduit (42), at least one mid-body conduit (44), and a trailing edge conduit (46). The conduits are operable to permit airflow through the root and into the cavity. Each conduit (42,44,46) has a centerline (58,74,88). The leading edge conduit (42) includes an inlet (48) having a forward side (50), a suction side (52), and a pressure side (56) that diverge from the centerline (58) of the leading edge conduit (42), and an aft side (52). Each of the mid-body conduits (44) includes an inlet (64) having a suction side (66) and a pressure side (68) that diverge from the centerline (74) of the mid-body conduit (44), and an aft side (70) and a forward side (72). The trailing edge conduit (46) includes an inlet (78) having a suction side (84) and a pressure side (86) that diverge from the centerline (88) of the trailing edge conduit (46). The trailing edge conduit inlet (78) further includes a forward side (82) and an aft side (80).

公开(公告)号：DE69312973T2

公开(公告)日：1998-03-19

申请号：DE69312973

申请日：1993-11-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W

IPC: F01D5/18 ,  F02K3/06

Abstract: A rotor blade having an integral platform with a cooled fillet is disclosed. Various construction details are developed which provide a cooling hole extending in proximity of the fillet to convectively cool the fillet. In a particular embodiment, a rotor blade having a integral platform and fillet includes a cooling hole extending between an internal cooling passage and a damper cavity. The cooling hole has a streamwise axis oriented in the direction to a line tangent to a midpoint of the fillet. The cooling hole directs a flow of cooling fluid radially inward and laterally outward, the cooling fluid flowing in proximity to the fillet to provide convective cooling.

公开(公告)号：DE69312973D1

公开(公告)日：1997-09-11

申请号：DE69312973

申请日：1993-11-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W

IPC: F01D5/18 ,  F02K3/06

Abstract: A rotor blade having an integral platform with a cooled fillet is disclosed. Various construction details are developed which provide a cooling hole extending in proximity of the fillet to convectively cool the fillet. In a particular embodiment, a rotor blade having a integral platform and fillet includes a cooling hole extending between an internal cooling passage and a damper cavity. The cooling hole has a streamwise axis oriented in the direction to a line tangent to a midpoint of the fillet. The cooling hole directs a flow of cooling fluid radially inward and laterally outward, the cooling fluid flowing in proximity to the fillet to provide convective cooling.

公开(公告)号：EP3077642A4

公开(公告)日：2017-07-19

申请号：EP14882627

申请日：2014-11-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGOWAN JOHN W

IPC: F02C7/143 ,  F02C3/107 ,  F02C7/10 ,  F02K3/077

CPC classification number: F02C7/143 ,  F02C3/107 ,  F02C7/08 ,  F02C7/10 ,  F02C7/185 ,  F02K3/077 ,  F05D2220/32 ,  F05D2250/30 ,  F05D2250/311 ,  F05D2260/211 ,  Y02T50/675

Abstract: A gas turbine engine includes a first stage compressor, an intercooler in fluid communication with the first stage compressor, and a second stage compressor in fluid communication with the intercooler. The engine also includes a combustor in fluid communication with the second stage compressor and a turbine in fluid communication with the combustor. The intercooler cools an air inflow from the first stage compressor and the recuperator heats the airflow traveling from the second stage compressor to the turbine exhaust. The intercooler and recuperator are arranged radially outward of the combustor.

Abstract translation: 燃气涡轮发动机包括第一级压缩机，与第一级压缩机流体连通的中间冷却器以及与中间冷却器流体连通的第二级压缩机。 发动机还包括与第二级压缩机流体连通的燃烧器和与燃烧器流体连通的涡轮机。 中间冷却器冷却来自第一级压缩机的空气流入，并且回流换热器加热从第二级压缩机行进到涡轮机废气的气流。 中间冷却器和换热器布置在燃烧器的径向外侧。

公开(公告)号：EP3039249A4

公开(公告)日：2017-03-29

申请号：EP14840790

申请日：2014-08-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LEWIS SCOTT D ,  MAGOWAN JOHN W

IPC: F01D5/08 ,  F01D11/00

CPC classification number: F01D5/141 ,  F01D5/02 ,  F01D5/081 ,  F01D5/18 ,  F01D9/041 ,  F01D11/006 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2250/32 ,  F05D2250/71 ,  F05D2260/221