Enhanced operability dual mode ramjet and scramjet engine ignition system

Patent metadata

Field	Value
Publication number	US-10451007-B1
Application number	US-201715438274-A
Country	US
Kind code	B1
Filing date	Feb 21, 2017
Priority date	Feb 21, 2017
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

An ignition system for a jet includes a squib. A solid propellant gas generator is ignitable by the squib and produces hot gas. An insulated hot gas accumulator is provided for storing the hot gas. A three-way hot gas valve is in fluid communication with the jet, the solid propellant gas generator, and the insulated hot gas accumulator. The three-way hot gas valve has a first condition establishing a first flow path from the solid propellant gas generator to the jet, a second condition establishing a second flow path from the solid propellant gas generator to the insulated hot gas accumulator, and a third condition establishing a third flow path from the insulated hot gas accumulator to the jet.

First claim

I claim:

1. An ignition system for an engine, the ignition system comprising:
an ignition source for producing hot gas;
an accumulator for storing the hot gas; and
a valve in fluid communication with the engine, the ignition source, and the accumulator, the valve selectively directing the hot gas from the ignition source to the engine to ignite the engine and selectively directing the hot gas from the ignition source to the accumulator to store the hot gas.

2. The ignition system according to claim 1 , wherein the valve is arranged to selectively direct the hot gas from the accumulator to the engine.

3. The ignition system according to claim 1 , wherein the engine is a jet engine.

4. The ignition system according to claim 3 , wherein the jet engine is a dual mode ramjet or a scramjet.

5. The ignition system according to claim 1 , wherein the ignition source includes a solid propellant gas generator.

6. The ignition system according to claim 5 , wherein the ignition system includes a squib for igniting the solid propellant gas generator.

7. The ignition system according to claim 1 , wherein the accumulator is thermally insulated.

8. A method of operating an engine comprising:
providing a valve that is in fluid communication with an ignition source, a hot gas accumulator, and the engine;
activating an ignition source to produce hot gas;
igniting the engine through use of the hot gas, the valve directing the hot gas from the ignition source to the engine; and
storing the hot gas in the hot gas accumulator after the step of igniting, the valve directing the hot gas from the ignition source to the hot gas accumulator.

9. The method according to claim 8 , further comprising sustaining combustion by preventing lean blowout using the hot gas stored in the hot gas accumulator.

10. The method according to claim 8 , further comprising reigniting the engine using the hot gas stored in the hot gas accumulator.

11. The method according to claim 10 , including directing the hot gas from the hot gas accumulator to the engine with the valve during the reigniting of the engine.

12. The method according to claim 8 , including thermally insulating the hot gas accumulator.

13. The method according to claim 8 , including providing the ignition source with a squib and a solid propellant gas generator.

14. The method according to claim 8 , wherein the valve is controlled to direct the hot gas from the ignition source to one of the hot gas accumulator and the engine depending on operational needs.

15. An ignition system for an engine, the ignition system comprising:
a squib;
a solid propellant gas generator for producing hot gas and ignitable by the squib;
an insulated hot gas accumulator for storing the hot gas; and
a three-way hot gas valve in fluid communication with the engine, the solid propellant gas generator, and the insulated hot gas accumulator, the three-way hot gas valve having a first condition establishing a first flow path from the solid propellant gas generator to the engine, a second condition establishing a second flow path from the solid propellant gas generator to the insulated hot gas accumulator, and a third condition establishing a third flow path from the insulated hot gas accumulator to the engine.

16. A vehicle comprising the ignition system of claim 15 .

Assignees

• Elia Shareil
• Northrop Grumman Systems Corp

Inventors

• Elia Shareil

Classifications

• F05D2220/80

  in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion · CPC title

• F02K9/95 Primary

  characterised by starting or ignition means or arrangements (safety devices F02K9/38) · CPC title

• F02K9/24

  Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges · CPC title

• F02K7/18

  Composite ram-jet/rocket engines · CPC title