公开(公告)号：US20240060429A1

公开(公告)日：2024-02-22

申请号：US17889542

申请日：2022-08-17

Applicant: General Electric Company

Inventor： Stephan Priebe ,  Giridhar Jothiprasad ,  Joseph Capozzi ,  Thomas Malkus ,  Michael Macrorie ,  Trevor H. Wood

IPC: F01D25/24 ,  F02C3/04 ,  F01D9/04

CPC classification number: F01D25/24 ,  F02C3/04 ,  F01D9/041 ,  F05D2230/60 ,  F05D2220/323

Abstract: A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).

公开(公告)号：US20230184125A1

公开(公告)日：2023-06-15

申请号：US17552294

申请日：2021-12-15

Applicant: General Electric Company

Inventor： Neelesh Sarawate ,  Stephan Priebe ,  Wojciech Sak

IPC: F01D11/12 ,  F01D25/24

CPC classification number: F01D11/122 ,  F01D25/24 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2250/294 ,  F05D2300/6111

Abstract: An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.

公开(公告)号：US12270306B2

公开(公告)日：2025-04-08

申请号：US17552294

申请日：2021-12-15

Applicant: General Electric Company

Inventor： Neelesh Sarawate ,  Stephan Priebe ,  Wojciech Sak

IPC: F01D11/12 ,  F01D25/24

Abstract: An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.

公开(公告)号：US20240060510A1

公开(公告)日：2024-02-22

申请号：US18234055

申请日：2023-08-15

Applicant: General Electric Company

Inventor： Stephan Priebe ,  Giridhar Jothiprasad ,  Joseph Capozzi ,  Thomas Malkus ,  Michael Macrorie ,  Trevor H. Wood

IPC: F04D29/52 ,  F04D29/32

CPC classification number: F04D29/526 ,  F04D29/324

Abstract: A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).