公开(公告)号：US11466572B2

公开(公告)日：2022-10-11

申请号：US17396029

申请日：2021-08-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Sue-Li Chuang

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/38 ,  F02C3/10

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a rotor hub and an array of blades circumferentially spaced about the rotor hub, a geared architecture, a compressor section and a turbine section. Each blade includes pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, adjacent blades in the array of blades including a first blade and a second blade, a facing pressure side of the first blade and a facing suction side of the second blade defining a channel having a width that varies in a chordwise direction between the facing pressure and suction sides at a given span position of the first and second blades. The width at each pressure side location of the first blade along the channel is defined as a minimum distance from the respective pressure side location to a location along the suction side of the second blade, and the width of the channel converges in the chordwise direction to establish a throat.

公开(公告)号：US20210372284A1

公开(公告)日：2021-12-02

申请号：US17396029

申请日：2021-08-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Sue-Li Chuang

IPC: F01D5/14 ,  F04D29/32 ,  F02C3/10 ,  F04D29/38

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a rotor hub and an array of blades circumferentially spaced about the rotor hub, a geared architecture, a compressor section and a turbine section. Each blade includes pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, adjacent blades in the array of blades including a first blade and a second blade, a facing pressure side of the first blade and a facing suction side of the second blade defining a channel having a width that varies in a chordwise direction between the facing pressure and suction sides at a given span position of the first and second blades. The width at each pressure side location of the first blade along the channel is defined as a minimum distance from the respective pressure side location to a location along the suction side of the second blade, and the width of the channel converges in the chordwise direction to establish a throat.