Aircraft propulsion system
AssigneeGeneral Electric Company
InventorsJeffrey D. Rambo, Brandon W. Miller, Scott G. Edens
Life of this patent
Estimating the term…
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.
Claims15
A propulsion system comprising:
- a turbine engine including a compressor section, a combustor, and a turbine section;
- a ramjet engine;
- 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, wherein the turbine engine inlet portion includes a converging/diverging inlet having a throat portion, the converging/diverging inlet converges from a forward end of the converging/diverging inlet to the throat portion and then diverges from the throat portion to an aft end of the converging/diverging inlet;
- an expansion turbine arranged in the turbine engine inlet portion upstream of the turbine engine;
- and
- a translating spike disposed within the turbine engine inlet portion upstream of the expansion turbine, wherein the translating spike engages the throat portion of the converging/diverging inlet, in a first operating state of the propulsion system, to restrict the inlet airflow to the expansion turbine such that the inlet airflow bypasses the expansion turbine, and the translating spike disengages the throat portion of the converging/diverging inlet, in a second operating state of the propulsion system, and to permit the inlet airflow through the expansion turbine to the turbine engine.
A method of operating a propulsion system, the propulsion system including (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 including (1) a converging/diverging inlet having a throat portion, the converging/diverging inlet converges from a forward end of the converging/diverging inlet to the throat portion and then diverges from the throat portion to an aft end of the converging/diverging inlet, (2) an expansion turbine arranged upstream of the turbine engine, (3) a translating spike disposed within the turbine engine inlet portion upstream of the expansion turbine, and (4) an intermediate inlet portion arranged between the expansion turbine and an inlet to the turbine engine, the intermediate inlet portion being actuated between an open state and a closed state, the method comprising:
- operating the propulsion system in a first operating state by (i) providing the inlet airflow through the ramjet inlet portion so as to provide a bypass airflow through the ramjet engine, (ii) actuating the translating spike to engage the throat portion of the converging/diverging inlet to restrict the inlet airflow from flowing through the expansion turbine such that the inlet airflow bypasses the expansion turbine, (iii) providing the inlet airflow through the intermediate inlet portion to the turbine engine, and (iv) operating the turbine engine to provide turbine engine propulsion;
- and
- operating the propulsion system in a second operating state by (v) providing the inlet airflow through the ramjet inlet portion to the ramjet engine, (vi) actuating the translating spike to disengage the throat portion of the converging/diverging inlet to permit the inlet airflow to flow through the expansion turbine to the turbine engine, (vii) restricting the inlet airflow from bypassing the expansion turbine and flowing into the intermediate inlet portion, (viii) operating the expansion turbine to expand and to cool the inlet airflow to generate a reduced temperature inlet airflow within the intermediate inlet portion, (ix) providing the reduced temperature inlet airflow through the intermediate inlet portion to the turbine engine, (x) and operating the turbine engine and the ramjet engine to provide ramjet engine propulsion.
Dependencies are inferred from the claim text.