公开(公告)号：US10760429B1

公开(公告)日：2020-09-01

申请号：US15868312

申请日：2018-01-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Xuedong Zhou ,  Evan K. Fink ,  Joseph C. Straccia ,  Joseph Wieser ,  Konstantinos Panagiotis Giannakopoulos

IPC: F01D5/00 ,  F01D5/16 ,  F01D5/34 ,  F01D9/04 ,  F02C3/06

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 3.45-3.75 inch (87.6-95.3 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 1.55-1.85 inch (39.4-47.0 mm). The airfoil element includes at least two of a first mode with a frequency of 424±10% Hz, a second mode with a frequency of 1401±10% Hz, a third mode with a frequency of 1770±10% Hz, a fourth mode with a frequency of 3336±10% Hz, a fifth mode with a frequency of 3378±10% Hz and a sixth mode with a frequency of 4141±10% Hz.

公开(公告)号：US10808544B1

公开(公告)日：2020-10-20

申请号：US15868181

申请日：2018-01-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Xuedong Zhou ,  Evan K. Fink ,  Joseph C. Straccia ,  Joseph Wieser ,  Konstantinos Panagiotis Giannakopoulos

IPC: F01D5/14 ,  F01D5/16 ,  F01D5/00 ,  F01D5/34 ,  F01D9/04 ,  F02C3/06

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 4.35-4.65 inch (110.5-118.1 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 2.45-2.75 inch (62.2-69.9 mm). The airfoil element includes at least two of a first mode with a frequency of 255±10% Hz, a second mode with a frequency of 818±10% Hz, a third mode with a frequency of 1439±10% Hz, a fourth mode with a frequency of 2035±10% Hz, a fifth mode with a frequency of 3033±10% Hz and a sixth mode with a frequency of 3740±10% Hz.

公开(公告)号：US20160208626A1

公开(公告)日：2016-07-21

申请号：US14599662

申请日：2015-01-19

Applicant: United Technologies Corporation

Inventor： Evan K. Fink ,  Joseph Steele

IPC: F01D5/30 ,  F01D5/14 ,  F02C3/04

CPC classification number: F01D5/3023 ,  F01D5/141 ,  F01D5/143 ,  F01D5/145 ,  F01D5/34 ,  F02C3/04 ,  F05D2240/24 ,  F05D2240/30 ,  Y02T50/673

Abstract: An integrally bladed rotor comprises a hub centered about an axis and having a plurality of blades extending radially outwardly of the axis across a span. Each of the blades includes an airfoil extending between a leading edge and a trailing edge, and having a pressure side and a suction side. The airfoil has a thicker portion at the trailing edge, and at a radially inner portion of the span, and over a limited percentage of the span, such that the thicker portion does not extend beyond 50 percent of the span. An axial distance is defined between the trailing edge and the leading edge. The thicker portion extends for less than 50 percent of the axial distance, and is on the pressure side. A gas turbine engine is also disclosed.

Abstract translation: 整体叶片转子包括以轴为中心的轮毂，并且具有跨过跨度径向向外延伸轴线的多个叶片。 每个叶片包括在前缘和后缘之间延伸并且具有压力侧和吸力侧的翼型件。 翼型件在后缘处具有较厚的部分，并且在跨度的径向内部部分和跨度的有限百分比之间，使得较厚部分不延伸超过跨度的50％。 在后缘和前缘之间限定轴向距离。 较厚的部分延伸小于轴向距离的50％，并且在压力侧。 还公开了一种燃气涡轮发动机。