公开(公告)号：US10774651B1

公开(公告)日：2020-09-15

申请号：US15869124

申请日：2018-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kurt R. Heinemann ,  Sumin Tao ,  Christopher B. Jelks ,  Xuedong Zhou ,  Mark David Ring ,  Konstantinos Panagiotis Giannakopolous ,  Lisa I. Brilliant

IPC: F01D5/14 ,  F01D5/16 ,  F01D5/28 ,  F01D5/34

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 2.85-3.15 inch (72.4-80.0 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 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506±10% Hz, a second mode with a frequency of 1732±10% Hz, a third mode with a frequency of 2268±10% Hz, a fourth mode with a frequency of 4007±10% Hz, a fifth mode with a frequency of 4851±10% Hz and a sixth mode with a frequency of 6416±10% Hz.

公开(公告)号：US11236616B1

公开(公告)日：2022-02-01

申请号：US15868499

申请日：2018-01-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kurt R. Heinemann ,  Sumin Tao ,  Christopher B. Jelks ,  Xuedong Zhou ,  Mark David Ring ,  Konstantinos Panagiotis Giannakopoulos ,  Kate Hudon ,  John Joseph Papalia

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

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 4.47-4.77 inch (113.5-121.2 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 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297±10% Hz, a second mode with a frequency of 1035±10% Hz, a third mode with a frequency of 1488±10% Hz, a fourth mode with a frequency of 1524±10% Hz, a fifth mode with a frequency of 2855±10% Hz and a sixth mode with a frequency of 4462±10% Hz.

公开(公告)号：US10815785B1

公开(公告)日：2020-10-27

申请号：US15869119

申请日：2018-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kurt R. Heinemann ,  Sumin Tao ,  Christopher B. Jelks ,  Xuedong Zhou ,  Mark David Ring ,  Konstantinos Panagiotis Giannakopoulos ,  Kate Hudon ,  John Joseph Papalia

IPC: F01D5/16 ,  F01D5/14 ,  F01D5/30

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 2.99-3.29 inch (75.9-83.6 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 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430±10% Hz, a second mode with a frequency of 1459±10% Hz, a third mode with a frequency of 2036±10% Hz, a fourth mode with a frequency of 3615±10% Hz, a fifth mode with a frequency of 4722±10% Hz and a sixth mode with a frequency of 5591±10% Hz.

公开(公告)号：US10415624B2

公开(公告)日：2019-09-17

申请号：US15606580

申请日：2017-05-26

Applicant: United Technologies Corporation

Inventor： Konstantinos Panagiotis Giannakopoulos ,  Christopher B. Jelks

IPC: F16B39/10 ,  F02C7/32 ,  F01D5/06 ,  F16B37/04 ,  F16B41/00 ,  F16B43/02

Abstract: A bolt retention clip for a gas turbine engine rotor assembly includes a main plate section defining a central aperture, the central aperture sized to receive a bolt therethrough. Also included is a pair of bolt retention tabs extending away from a first face of the main plate section to axially retain a head of the bolt. Further included is a first clip retaining tab extending away from the first face of the main plate section for insertion into a groove of a rotor structure. Yet further included is a second clip retaining tab extending away from a second face of the main plate section for engagement with an edge of the rotor structure.

公开(公告)号：US20180340565A1

公开(公告)日：2018-11-29

申请号：US15606580

申请日：2017-05-26

Applicant: United Technologies Corporation

Inventor： Konstantinos Panagiotis Giannakopoulos ,  Christopher B. Jelks

IPC: F16B39/10 ,  F02C7/32

CPC classification number: F16B39/10 ,  F01D5/066 ,  F02C7/32 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2260/31 ,  F16B37/043 ,  F16B41/002 ,  F16B43/025

Abstract: A bolt retention clip for a gas turbine engine rotor assembly includes a main plate section defining a central aperture, the central aperture sized to receive a bolt therethrough. Also included is a pair of bolt retention tabs extending away from a first face of the main plate section to axially retain a head of the bolt. Further included is a first clip retaining tab extending away from the first face of the main plate section for insertion into a groove of a rotor structure. Yet further included is a second clip retaining tab extending away from a second face of the main plate section for engagement with an edge of the rotor structure.