公开(公告)号：SG10201705687PA

公开(公告)日：2017-08-30

申请号：SG10201705687P

申请日：2013-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAYER ROBERT RUSSELL ,  KRAMER GEORGE J ,  PALMER PAUL W

Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.

公开(公告)号：SG11201402940PA

公开(公告)日：2014-11-27

申请号：SG11201402940P

申请日：2013-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAYER ROBERT RUSSELL ,  KRAMER GEORGE J ,  PALMER PAUL W

IPC: F01D25/16

Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.

公开(公告)号：EP3090148A4

公开(公告)日：2017-09-06

申请号：EP14871441

申请日：2014-08-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GARCIA IGOR S ,  LIU SHU ,  MAYER ROBERT RUSSELL ,  BAKER ERIC ,  ERNST STEPHANIE ,  GRANT FERNANDO K ,  MILLER ANDREW S ,  BALAWAJDER PETER ,  PALMER PAUL W

IPC: F01D25/24 ,  F02C7/00

CPC classification number: F01D21/04 ,  F01D21/045 ,  F01D25/24 ,  F02C3/04 ,  F04D19/002 ,  F04D29/023 ,  F04D29/526 ,  F05D2220/32 ,  F05D2240/14 ,  F05D2240/35 ,  F05D2250/283 ,  F05D2300/505 ,  F05D2300/6012 ,  F05D2300/6032 ,  F05D2300/6033

Abstract: A gas turbine engine includes a containment ring to contain liberated compressor and turbine blades and blade fragments within a core assembly. The combination of a containment gap between the core case and the containment ring and a containment layer disposed in the gap helps dissipate the energy generated by loose body impacts on the core assembly. The containment layer deforms, deflects, and/or redirects the impact energy acting in a radial direction, thereby to improve containment.

Abstract translation: 燃气涡轮发动机包括容纳环，以将释放的压缩机和涡轮机叶片以及叶片片段容纳在核心组件内。 核心壳与密封环之间的密封间隙和布置在间隙中的密封层的组合有助于消散松散的身体对核心组件上的冲击所产生的能量。 包容层使沿径向作用的冲击能量变形，偏转和/或重定向，由此改善容纳。

公开(公告)号：EP3094830A4

公开(公告)日：2017-11-29

申请号：EP14872667

申请日：2014-08-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LIU SHU ,  MAYER ROBERT RUSSELL ,  PALMER PAUL W ,  BALAWAJDER PETER ,  GARCIA IGOR S ,  PIMENTA DAVID C ,  ERNST STEPHANIE ,  GRANT FERNANDO K ,  BAKER ERIC ,  MILLER ANDREW S

IPC: F01D21/04 ,  F01D25/24

CPC classification number: F01D25/26 ,  F01D21/045 ,  F01D25/24 ,  F02C3/04 ,  F02K3/06 ,  F04D29/522 ,  F04D29/526 ,  F05D2220/32 ,  F05D2250/283 ,  F05D2250/29 ,  F05D2300/506 ,  F23R3/002

Abstract: A gas turbine engine includes a core assembly with a core case having a containment section for containing liberated compressor and turbine blades and blade fragments. The containment section includes first and second containment layers and the containment section is configured to have a non-linear rate of energy dissipation across the first and second containment layers, thereby to improve containment of blades and blade fragments.

公开(公告)号：EP2809891A4

公开(公告)日：2015-11-04

申请号：EP13775408

申请日：2013-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAYER ROBERT RUSSELL ,  KRAMER GEORGE J ,  PALMER PAUL W

IPC: F01D25/16 ,  F01D25/24

CPC classification number: F02C7/06 ,  F01D25/164 ,  F01D25/243 ,  F02C3/045 ,  F02C7/20 ,  F02C7/36 ,  F05D2220/32 ,  F05D2240/90 ,  F05D2260/30 ,  F05D2260/40311 ,  F23R3/002 ,  F23R3/60 ,  Y02T50/671