公开(公告)号：US10570755B2

公开(公告)日：2020-02-25

申请号：US14617614

申请日：2015-02-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Scott C. Billings ,  William R. Graves ,  Jason Elliott ,  David P. Houston ,  Ethan C. Drew

IPC: F01D5/30 ,  F02C3/04

Abstract: A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.

公开(公告)号：US20150110636A1

公开(公告)日：2015-04-23

申请号：US14170985

申请日：2014-02-03

Applicant: United Technologies Corporation

Inventor： Jay T. Abraham ,  Ethan C. Drew ,  Scott C. Billings ,  Michael A. Weisse ,  James O. Hansen ,  Venkatarama K. Seetharaman

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/3092 ,  F05D2220/36 ,  F05D2300/614 ,  F05D2300/701 ,  Y02T50/671

Abstract: A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate.

Abstract translation: 燃气涡轮发动机的风扇叶片包括翼型件，容纳在轮毂的槽中的根部和覆盖根部的至少一部分并由整体结合的织造复合层压板制成的耐磨垫片。

公开(公告)号：US10781827B1

公开(公告)日：2020-09-22

申请号：US15872171

申请日：2018-01-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jason Elliott ,  Daniel C. Falk ,  Myron L. Klein ,  Ethan C. Drew ,  James H. Moffitt ,  Darryl Whitlow ,  Byron R. Monzon ,  Jay Thomas Abraham ,  William R. Graves

IPC: F04D29/32 ,  F04D29/38 ,  F02C3/04 ,  F02K3/06 ,  F04D29/66 ,  F01D5/16

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 27.5-28.5 inches (699-724 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 34±10% Hz, a second mode with a frequency of 90±10% Hz, a third mode with a frequency of 178±10% Hz, a fourth mode with a frequency of 222±10% Hz, a fifth mode with a frequency of 307±10% Hz and a sixth mode with a frequency of 389±10% Hz.

公开(公告)号：US10273816B2

公开(公告)日：2019-04-30

申请号：US14170985

申请日：2014-02-03

Applicant: United Technologies Corporation

Inventor： Jay T. Abraham ,  Ethan C. Drew ,  Scott C. Billings ,  Michael A. Weisse ,  James O. Hansen ,  Venkatarama K. Seetharaman

IPC: F01D5/30

Abstract: A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate.

公开(公告)号：US20160230572A1

公开(公告)日：2016-08-11

申请号：US14617614

申请日：2015-02-09

Applicant: United Technologies Corporation

Inventor： Scott C. Billings ,  William R. Graves ,  Jason Elliott ,  David P. Houston ,  Ethan C. Drew

IPC: F01D5/30 ,  F02C3/04

Abstract: A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.

Abstract translation: 风扇叶片的燕尾根被配置为在燃气涡轮发动机的风扇组件内操作。 燕尾根沿着燕尾根的外表面施加压缩残余应力层，防止在燃气轮机发动机运行时在燕尾根内形成裂纹。 为了进一步保护和结构地增强燕尾根，在燕尾根上设置磨损覆盖物。 磨损覆盖物可以由复合层压层组成，该复合层压层结合到燕尾榫根部的金属芯上，当燃气涡轮发动机运行时，它可以提供燕尾根的附加开裂保护。