公开(公告)号：US11773866B2

公开(公告)日：2023-10-03

申请号：US17590115

申请日：2022-02-01

Applicant: Raytheon Technologies Corporation

Inventor： Simon W. Evans ,  Yuan Dong ,  Sean Nolan

IPC: F04D29/38 ,  F01D5/14 ,  F04D19/02 ,  F04D29/32

CPC classification number: F04D29/384 ,  F01D5/145 ,  F04D19/02 ,  F04D29/324 ,  F05D2210/30 ,  F05D2220/3216 ,  F05D2240/307 ,  F05D2260/821 ,  F05D2270/3013 ,  Y02T50/60

Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.

公开(公告)号：US20220154728A1

公开(公告)日：2022-05-19

申请号：US17590115

申请日：2022-02-01

Applicant: Raytheon Technologies Corporation

Inventor： Simon W. Evans ,  Yuan Dong ,  Sean Nolan

IPC: F04D29/38 ,  F01D5/14 ,  F04D19/02 ,  F04D29/32

Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.

公开(公告)号：US11767764B1

公开(公告)日：2023-09-26

申请号：US17031221

申请日：2020-09-24

Applicant: Raytheon Technologies Corporation

Inventor： Haiyun Li ,  Eliannah Hunderfund ,  Sean Nolan

IPC: F01D5/16 ,  F01D5/34 ,  F01D5/14 ,  F02C3/06

CPC classification number: F01D5/16 ,  F01D5/141 ,  F01D5/34 ,  F02C3/06 ,  F05D2220/321 ,  F05D2230/80 ,  F05D2240/30 ,  F05D2260/96 ,  F05D2300/175 ,  F05D2300/522

Abstract: A turbomachine airfoil element includes an airfoil having 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 0.83-0.93 inch (21.1-23.6 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 0.80-0.90 inch (20.4-22.9 mm). The airfoil element includes at least two of a first mode with a frequency is 3135±10% Hz, a second mode with a frequency is 6634±10% Hz, a third mode with a frequency is 13260±10% Hz, a fourth mode with a frequency is 16838±10% Hz and a fifth mode with a frequency is 17980±10% Hz.