公开(公告)号：US20240191675A1

公开(公告)日：2024-06-13

申请号：US18065143

申请日：2022-12-13

Applicant: General Electric Company

Inventor： Jeffrey D. Rambo ,  Scott G. Edens

IPC: F02K7/16 ,  F02C6/00 ,  F02C7/22

CPC classification number: F02K7/16 ,  F02C6/00 ,  F02C7/22

Abstract: A propulsion system includes a turbine engine, and a ramjet engine arranged in parallel with the turbine engine, a fuel storage tank that stores a fuel, such as an ammonia-based fuel, a heat exchanger through which the fuel passes to obtain gaseous (or supercritical) fuel components of the fuel, and a separator that separates the gaseous fuel components into a first fuel component and a second fuel component. The first fuel component is provided to the ramjet engine for ramjet combustion and/or to the turbine engine for turbine combustion, in a high speed operating state of the propulsion system, while the second fuel component may be provided to an inlet of the turbine engine for the turbine combustion.

公开(公告)号：US12110827B1

公开(公告)日：2024-10-08

申请号：US18311660

申请日：2023-05-03

Applicant: General Electric Company

Inventor： Jeffrey D. Rambo ,  Scott G. Edens ,  Michael Joseph Murray

IPC: F02C7/236 ,  F02C7/32

CPC classification number: F02C7/236 ,  F02C7/32 ,  F05D2220/323 ,  F05D2270/07

Abstract: A turbo engine for an aircraft includes a gas turbine engine having a combustion section and a fuel system to provide pressurized fuel to the combustion section. The fuel system includes a fuel tank and a boost pump and a main pump driven by an accessory gearbox that is powered by a shaft of the turbo engine. The boost pump and the main pump are arranged in series. The fuel system also includes an auxiliary pump and a controller to operate the fuel system in (1) a first mode in which the boost pump and the main pump produce pressurized fuel for the turbo engine and the auxiliary pump is deactivated, and (2) a second mode in which the auxiliary pump is activated and produces the pressurized fuel for the turbo engine while bypassing the boost pump and the main pump.

公开(公告)号：US12116956B2

公开(公告)日：2024-10-15

申请号：US18065143

申请日：2022-12-13

Applicant: General Electric Company

Inventor： Jeffrey D. Rambo ,  Scott G. Edens

IPC: F02K7/16 ,  F02C3/20 ,  F02C6/00

CPC classification number: F02K7/16 ,  F02C3/20 ,  F02C6/00

Abstract: A propulsion system includes a turbine engine, and a ramjet engine arranged in parallel with the turbine engine, a fuel storage tank that stores a fuel, such as an ammonia-based fuel, a heat exchanger through which the fuel passes to obtain gaseous (or supercritical) fuel components of the fuel, and a separator that separates the gaseous fuel components into a first fuel component and a second fuel component. The first fuel component is provided to the ramjet engine for ramjet combustion and/or to the turbine engine for turbine combustion, in a high speed operating state of the propulsion system, while the second fuel component may be provided to an inlet of the turbine engine for the turbine combustion.

公开(公告)号：US20240229726A1

公开(公告)日：2024-07-11

申请号：US18152903

申请日：2023-01-11

Applicant: General Electric Company

Inventor： Jeffrey D. Rambo ,  Brandon W. Miller ,  Scott G. Edens

IPC: F02C9/18 ,  F02C3/04 ,  F02C7/057

CPC classification number: F02C9/18 ,  F02C3/04 ,  F02C7/057 ,  F05D2220/10 ,  F05D2220/3217 ,  F05D2220/323

Abstract: A propulsion system includes (a) a turbine engine including a compressor section, a combustor, and a turbine section, (b) a ramjet engine, and (c) an inlet section including a turbine engine inlet portion and a ramjet inlet portion, the inlet section providing an inlet airflow to the turbine engine and to the ramjet engine. The turbine engine inlet portion includes an expansion turbine arranged upstream of the compressor section.

公开(公告)号：US20240191674A1

公开(公告)日：2024-06-13

申请号：US18065137

申请日：2022-12-13

Applicant: General Electric Company

Inventor： Jeffrey D. Rambo ,  Scott G. Edens

IPC: F02K7/16 ,  F02C6/20

CPC classification number: F02K7/16 ,  F02C6/20 ,  F05D2220/10

Abstract: A propulsion system includes a turbine engine and a ramjet engine. A turbine engine inlet section restriction device permits an inlet airflow to a turbine engine inlet in a first (low speed) operating state of the propulsion system, and restricts the inlet airflow to the turbine engine inlet in a second (high speed) operating state of the propulsion system. A combustor inlet flow control device, in the first operating state, provides an airflow from a compressor to the turbine engine combustor, and restricts an airflow from a ramjet bleed air passage, and, in the second operating state, provides a ramjet inlet bleed airflow to the turbine engine combustor, while restricting airflow from the compressor. In the second operating state, the turbine engine drives at least one accessory gearbox to drive at least one accessory component.