Internal detonation engine, hybrid engines including the same, and methods of making and using the same

• US 9,188,002 B2
• Filed: 07/19/2013
• Issued: 11/17/2015
• Est. Priority Date: 07/24/2012
• Status: Expired due to Fees

• Current Assignee: Brent Wei-Teh Lee
• Original Assignee: Brent Wei-Teh Lee
• Inventors: Lee, Brent Wei-Teh
• Primary Examiner(s): NGUYEN, ANDREW H
• Application Number:
  US13/946,829
• Publication Number:
  US 20140338358A1
• Time in Patent Office: 851 Days
• Field of Search: 60/397.6, 60 3978- 3981, 60 3938- 394, 602/47, 123/80.R, 123/80.BA, 123/80.BB, 431/1
• US Class Current: 1/1
• CPC Class Codes: F01B 21/04 the machines or engines being not all of reciprocating-piston type, e.g. of reciprocating steam engine with steam turbine
• CPC Class Codes: F01L 1/02 Valve drive transmitting-gear between valve drive and valve F01L1/12
• CPC Class Codes: F01L 5/045 Piston-type or cylinder-type valves arranged above the piston and coaxial with the cylinder axis
• CPC Class Codes: F01L 7/06 with disc type valves
• CPC Class Codes: F02B 69/06 for different cycles, e.g. convertible from two-stroke to four stroke
• CPC Class Codes: F02C 5/02 characterised by the arrangement of the combustion chamber in the chamber in the plant combustion chambers per se F23R
• CPC Class Codes: F02C 5/12 the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
• CPC Class Codes: F02K 7/06 with combustion chambers having valves
• CPC Class Codes: F05B 2220/302 in gas turbines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Hybrid internal detonation-gas turbine engines incorporating detonation or pulse engine technology (such as an internal detonation engine), and methods of manufacturing and using the same are disclosed. The internal detonation engine includes a detonation chamber having a fuel igniter therein, a stator at one end of the detonation chamber having at least a first opening to receive fuel, a rotor adjacent to the stator, and an energy transfer mechanism configured to convert energy from igniting or detonating the fuel to mechanical energy. The detonation chamber and fuel igniter are configured to ignite or detonate a fuel in the detonation chamber. Either the stator or the detonation chamber has a second opening to exhaust detonation gas(es). The rotor has one or more third openings therein configured to overlap with at least the first opening as the rotor rotates.

Claims

1. An internal detonation engine, comprising:

a) a detonation chamber having a fuel igniter therein, the detonation chamber and fuel igniter configured to ignite or detonate a fuel in the detonation chamber;

b) a first stator at a first end of the detonation chamber having at least a first opening receiving the fuel, the detonation chamber having a second opening to exhaust detonation gas(es);

c) a first rotor adjacent to the first stator and driven by an axial shaft, the first rotor having one or more third openings therein configured to overlap with at least the first opening as the first rotor rotates; and

d) an energy transfer mechanism configured to transfer energy from igniting or detonating the fuel to mechanical energy, wherein the energy transfer mechanism includes a mechanism that drives the axial shaft,

wherein the detonation chamber further comprises a second stator and the engine further comprises a second rotor, the second opening is in the second stator, and the second rotor has one or more fourth openings therein configured to overlap with the second opening and seal the second opening when none of the one or more fourth openings overlap with the second opening.

2. The engine of claim 1, wherein the mechanism that drives the axial shaft comprises a drive mechanism configured to receive the mechanical energy.

3. The engine of claim 2, wherein the drive mechanism comprises one or more rods connected to the energy transfer mechanism and a crankshaft receiving the mechanical energy from at least one of the one or more rods.

4. The engine of claim 3, wherein the crankshaft drives a gear or wheel, the gear or wheel in turn driving one or more shafts or belts.

5. The engine of claim 1, further comprising a lubricant and/or a surface coating on the first rotor, the surface coating reducing friction between the first rotor and the first stator.

6. A hybrid internal detonation-turbine engine, comprising:

a) the internal detonation engine of claim 1;

b) a rotatable shaft; and

c) a compressor, upstream from the first stator and first rotor;

wherein the mechanism that drives the axial shaft comprises one or more turbines rotatably fixed to the rotatable shaft, downstream from the internal detonation engine.

7. The hybrid internal detonation-turbine engine of claim 6, wherein the compressor comprises one or more rotary fans rotatably fixed to the rotatable shaft, and the one or more turbines are configured to rotate the one or more rotary fans and compress air before the air is taken into the detonation chamber.

8. A method of converting energy, comprising:

a) introducing the fuel into the detonation chamber of the internal detonation engine of claim 1 through the first opening in the first stator at the first end of the detonation chamber;

b) igniting or detonating the fuel in the detonation chamber;

c) exhausting detonation gas(es) through the second opening in either the first stator or the detonation chamber;

d) converting energy from igniting or detonating the fuel to mechanical energy at one or more shafts, wheels, or gears; and

e) rotating the first rotor, the one or more third openings in the first rotor configured to overlap with at least the first opening as the first rotor rotates and otherwise seal the first opening when none of the one or more third openings overlap with the first opening.

9. The method of claim 8, wherein converting energy from igniting or detonating the fuel to mechanical energy comprises driving one or more rods connected to a crankshaft that receives the mechanical energy from at least one of the one or more rods.

10. The method of claim 9, wherein the crankshaft drives a gear or wheel, and the gear or wheel in turn driving one or more shafts or belts.

11. The method of claim 8, further comprising lubricating a surface of the first rotor to reduce friction between the first rotor and the first stator.

12. The method of claim 8, further comprising rotating a second rotor adjacent to the second stator.

13. The method of claim 8, further comprising rotating one or more turbines rotatably fixed to a rotatable shaft using the mechanical energy, thereby rotating one or more rotary fans rotatably fixed to the rotatable shaft on an opposite side of the detonation chamber from the one or more turbines and compressing air before the air is taken into the detonation chamber.

14. The engine of claim 1, wherein the second stator is at a second end of the detonation chamber opposite to the first end.

15. The method of claim 12, wherein the second stator is at a second end of the detonation chamber opposite to the first end.

16. The engine of claim 1, wherein the first stator has a plurality of first openings receiving the fuel, and the first rotor has a plurality of third openings therein configured to overlap with the first openings as the first rotor rotates.

17. The engine of claim 16, wherein the second stator has a plurality of second openings to exhaust detonation gas(es), and the second rotor has a plurality of fourth openings therein configured to overlap with the second openings and seal the second openings when none of the fourth openings overlap with any of the second openings.

18. The method of claim 12, wherein the first stator has a plurality of first openings receiving the fuel, and the first rotor has a plurality of third openings therein configured to overlap with the first openings as the first rotor rotates.

19. The method of claim 18, wherein the second stator has a plurality of second openings to exhaust detonation gas(es), and the second rotor has a plurality of fourth openings therein configured to overlap with the second openings and seal the second openings when none of the fourth openings overlap with any of the second openings.