公开(公告)号：US10060263B2

公开(公告)日：2018-08-28

申请号：US14827059

申请日：2015-08-14

Applicant: United Technologies Corporation

Inventor： Daniel K. Van Ness ,  Mark A. Stephens ,  Edward J. Gallagher ,  Joseph C. Straccia ,  Vikram A. Kumar

IPC: F02C1/00 ,  F01D5/14 ,  F01D9/04 ,  F02C3/04 ,  F04D29/32 ,  F04D29/54

CPC classification number: F01D5/141 ,  F01D5/142 ,  F01D9/041 ,  F02C3/04 ,  F04D29/324 ,  F04D29/544 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/301 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/35 ,  F05D2250/71 ,  Y02T50/672 ,  Y02T50/673

Abstract: A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.

公开(公告)号：US20160076380A1

公开(公告)日：2016-03-17

申请号：US14827059

申请日：2015-08-14

Applicant: United Technologies Corporation

Inventor： Daniel K. Van Ness ,  Mark A. Stephens ,  Edward J. Gallagher ,  Joseph C. Straccia ,  Vikram A. Kumar

IPC: F01D5/14 ,  F02C3/04 ,  F04D29/54 ,  F01D9/04 ,  F04D29/32

CPC classification number: F01D5/141 ,  F01D5/142 ,  F01D9/041 ,  F02C3/04 ,  F04D29/324 ,  F04D29/544 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/301 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/35 ,  F05D2250/71 ,  Y02T50/672 ,  Y02T50/673

Abstract: A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.

Abstract translation: 描述燃气涡轮发动机部件。 燃气涡轮发动机部件包括内径边缘，外径边缘，后缘和前缘。 前缘在前缘的整个跨度的整个跨度上具有正（后）气动扫描。 燃气涡轮发动机部件在组件的基本上整个跨度上具有大于50度的外倾角。 燃气涡轮发动机部件可以具有径向方向上的部件的不对称切向堆叠。