US 2026/0036090 A1 · CRYOGENIC FUEL START UP SYSTEM

Abstract

An aircraft propulsion system includes a core engine that includes a combustor where a cryogenic fuel is mixed with compressed air and ignited to generate an exhaust gas flow, a propulsive fan that is driven by shaft power generated by the core engine, a cryogenic fuel system that includes a cryogenic fuel storage tank and a fuel flow path for routing fuel to the combustor of the core engine, an engine start system that includes a first stage that generates a first quantity of thermal energy for heating a first portion of fuel and a second stage that utilizes the heated first portion of fuel to generate a second quantity of thermal energy for heating a second portion of fuel, the second quantity of thermal energy is greater than the first quantity of thermal energy and the second portion of fuel is communicated to the core engine.

Claims19

Dependent claims

An aircraft propulsion system comprising:

a core engine comprising a combustor where a cryogenic fuel is mixed with compressed air and ignited to generate an exhaust gas flow;
a propulsive fan driven by shaft power generated by the core engine;
a cryogenic fuel system comprising a cryogenic fuel storage tank and a primary fuel flow path for routing fuel to the combustor of the core engine;
an engine start system comprising a first stage generating a first quantity of thermal energy for heating a first portion of fuel and a second stage that utilizes the heated first portion of fuel to generate a second quantity of thermal energy for heating a second portion of fuel, wherein the first stage comprises a blower to generate an airflow separate from the core engine, the airflow provides the first quantity of thermal energy communicated into the first portion of the fuel and is communicated to the second stage after heating the first portion of the fuel and used for generating the second quantity of thermal energy, and the second quantity of thermal energy is greater than the first quantity of thermal energy and the second portion of fuel is communicated to the core engine.

1 more element

A method of assembling an aircraft propulsion system comprising

assembling a core engine comprising a combustor where a cryogenic fuel is mixed with compressed air and ignited to generate an exhaust gas flow;
assembling a propulsive fan configured to be driven by shaft power generated by the core engine;
assembling a cryogenic fuel system to comprise a cryogenic fuel storage tank, and a fuel flow path for routing a cryogenic fuel to the combustor;
and
assembling an engine start system comprising a first stage configured to generate a first quantity of thermal energy for heating a first portion of fuel and a second stage configured to utilize the heated first portion of fuel to generate a second quantity of thermal energy for heating a second portion of fuel, wherein assembly of the first stage comprises assembling a motor to drive a blower configured to generate an airflow that provides the first quantity of thermal energy communicated into the first portion of fuel and communicate the generated airflow to the second stage to be used for generating the second quantity of thermal energy such that the second quantity of thermal energy is greater than the first quantity of thermal energy and the second portion of fuel is communicated to the core engine.

2 more elements

Dependencies are inferred from the claim text.

Cryogenic fuel start up system

Life of this patent

Cryogenic fuel start up system

Life of this patent

Abstract

Claims19