SYSTEM AND METHOD FOR FORMING A NOZZLE INLET OF A NOZZLE

    公开(公告)号:US20240227050A9

    公开(公告)日:2024-07-11

    申请号:US17971108

    申请日:2022-10-21

    CPC classification number: B23H9/10 B23H3/10 B23H9/16

    Abstract: A system for forming a nozzle inlet of a nozzle includes a nozzle body and an electro-chemical machining (ECM) assembly. The nozzle body includes an external surface. The nozzle body forms a nozzle orifice and a manifold passage. The nozzle orifice extends through the nozzle body between and to a nozzle inlet and a nozzle outlet. The nozzle inlet is disposed at the manifold passage. The nozzle outlet is disposed at the external surface. The ECM assembly is installed on the nozzle body. The ECM assembly includes a machining tool and a flexible line. The machining tool is disposed at the nozzle inlet. The flexible line is attached to the machining tool. The flexible line extends through the nozzle outlet from the machining tool to an exterior of the nozzle body.

    SYSTEM AND METHOD FOR FORMING A NOZZLE INLET OF A NOZZLE

    公开(公告)号:US20240131607A1

    公开(公告)日:2024-04-25

    申请号:US17971108

    申请日:2022-10-20

    CPC classification number: B23H9/10 B23H3/10 B23H9/16

    Abstract: A system for forming a nozzle inlet of a nozzle includes a nozzle body and an electro-chemical machining (ECM) assembly. The nozzle body includes an external surface. The nozzle body forms a nozzle orifice and a manifold passage. The nozzle orifice extends through the nozzle body between and to a nozzle inlet and a nozzle outlet. The nozzle inlet is disposed at the manifold passage. The nozzle outlet is disposed at the external surface. The ECM assembly is installed on the nozzle body. The ECM assembly includes a machining tool and a flexible line. The machining tool is disposed at the nozzle inlet. The flexible line is attached to the machining tool. The flexible line extends through the nozzle outlet from the machining tool to an exterior of the nozzle body.

    BURNER FOR AN AIRCRAFT GAS TURBINE ENGINE

    公开(公告)号:US20250052418A1

    公开(公告)日:2025-02-13

    申请号:US18233159

    申请日:2023-08-11

    Abstract: An assembly for a gas turbine engine includes at least one burner and a hydrogen manifold. The at least one burner includes an outer nozzle and an inner nozzle. The outer nozzle forms a combustion chamber. The outer nozzle includes an outer converging axial portion and an outer diverging axial portion. The outer converging axial portion is disposed at an upstream axial end of the outer nozzle. The outer diverging axial portion is disposed axially downstream of the outer converging axial portion. The inner nozzle includes an inner converging axial portion at a downstream axial end of the inner nozzle. The inner converging axial portion is disposed within the outer converging axial portion to form an annular gap between the outer converging axial portion and the inner converging axial portion. The hydrogen manifold is disposed at the upstream axial end. The hydrogen manifold is connected in fluid communication with the annular gap.

Patent Agency Ranking