公开(公告)号：US10815832B2

公开(公告)日：2020-10-27

申请号：US16012396

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Peter Staffier ,  Paul W. Palmer ,  Anders C. Olson ,  Nicholas W. Kantany ,  Eric Baker

IPC: F01D25/24 ,  F01D25/00 ,  F01D25/30

Abstract: A turbine exhaust case is provided for a gas turbine engine. This turbine exhaust case includes a first gas turbine engine exhaust case, a second gas turbine engine exhaust case, a strut and a fastener. The second gas turbine engine exhaust case includes a flange and a bracket. The strut is coupled to the first case and the second case. The fastener fastens the flange and the strut. The second gas turbine engine exhaust case is co-axial with the first gas turbine engine exhaust case. The strut contacts the bracket when the engine is powered-on.

公开(公告)号：US20190383170A1

公开(公告)日：2019-12-19

申请号：US16012396

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Peter Staffier ,  Paul W. Palmer ,  Anders C. Olson ,  Nicholas W. Kantany ,  Eric Baker

IPC: F01D25/24 ,  F01D25/30 ,  F01D25/00

Abstract: A turbine exhaust case is provided for a gas turbine engine. This turbine exhaust case includes a first gas turbine engine exhaust case, a second gas turbine engine exhaust case, a strut and a fastener. The second gas turbine engine exhaust case includes a flange and a bracket. The strut is coupled to the first case and the second case. The fastener fastens the flange and the strut. The second gas turbine engine exhaust case is co-axial with the first gas turbine engine exhaust case. The strut contacts the bracket when the engine is powered-on.

公开(公告)号：US20160341075A1

公开(公告)日：2016-11-24

申请号：US15106615

申请日：2014-08-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Shu Liu ,  Robert Russell Mayer ,  Paul W. Palmer ,  Peter Balawajder ,  Igor S. Garcia ,  David C. Pimenta ,  Stephanie Ernst ,  Fernando K. Grant ,  Eric Baker ,  Andrew S. Miller

IPC: F01D25/26 ,  F23R3/00 ,  F04D29/52 ,  F02C3/04 ,  F02K3/06

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.

Abstract translation: 燃气涡轮发动机包括具有芯壳的芯组件，所述芯壳具有用于容纳释放的压缩机和涡轮叶片和叶片碎片的容纳部分。 容纳部分包括第一和第二容纳层，并且容纳部分被配置为具有穿过第一和第二容纳层的非线性能量消耗速率，从而改善叶片和叶片碎片的收容。

公开(公告)号：US20160341070A1

公开(公告)日：2016-11-24

申请号：US15106566

申请日：2014-08-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Igor S. Garcia ,  Shu Liu ,  Robert Russell Mayer ,  Eric Baker ,  Stephanie Ernst ,  Fernando K. Grant ,  Andrew S. Miller ,  Peter Balawajder ,  Paul W. Palmer

IPC: F01D21/04 ,  F04D19/00 ,  F04D29/52 ,  F02C3/04 ,  F01D25/24

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，以容纳释放的压缩机和涡轮叶片以及芯组件内的叶片碎片。 芯壳与容纳环之间的容纳间隙和设置在间隙中的容纳层的组合有助于消散由芯体组件上的松动的身体撞击产生的能量。 容纳层使沿径向作用的冲击能量变形，偏转和/或重定向，从而改善容纳。