Constant volume combustor having a rotating wave rotor

• US 7,621,118 B2
• Filed: 10/24/2006
• Issued: 11/24/2009
• Est. Priority Date: 07/03/2002
• Status: Active Grant

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Snyder, Philip H., Emmerson, Calvin W.
• Primary Examiner(s): RODRIGUEZ, WILLIAM H
• Application Number:
  US11/585,689
• Publication Number:
  US 20070157625A1
• Time in Patent Office: 1,127 Days
• Field of Search: 602/47, 602/10, 60/393.4, 60/397.6, 60/393.8, 607/72, 607/50
• US Class Current: 60/247
• CPC Class Codes: F23C 15/00 Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass for generating combustion products of high pressure or high velocity F23R7/00; starting devices F23D11/42
• CPC Class Codes: F23R 3/56 Combustion chambers having rotary flame tubes
• CPC Class Codes: F23R 7/00 Intermittent or explosive combustion chambers

Abstract

A constant volume combustor device includes, in one form, a detonative combustion. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings. The constant volume combustor device includes a rotor having a number of fluid passageways that rotate about an axis. End plates having at least one inlet port and at least one outlet port are located on either end of the rotor. Relatively compressed air enters the rotor through the at least one inlet port, is burned with fuel in a pulsed combustion process, and exits at least one exit port. The pulsed combustion process can be a pulsed detonation combustion process or a pulsed deflagration combustion process.

Claims

1. A method, comprising:

(a) rotating a wave rotor having a passageway with a first end and a second end;

(b) introducing a quantity of working fluid into a passageway through the first end of the passageway;

(c) delivering a quantity of fuel into the passageway through the first end of the passageway;

(d) burning the fuel within the passageway and creating a combusted gas;

(e) compressing a portion of the working fluid within the passageway to define a buffer gas;

(f) discharging a first portion of the buffer gas from the passageway through the first end of the passageway;

(g) discharging a portion of the combusted gas from the passageway through the second end of the passageway;

(h) retaining a second portion of the buffer gas within the passageway at the first end; and

(i) routing the first portion of the buffer gas from said discharging back into the passageway through the first end of the passageway.

2. The method of claim 1, wherein at least a portion of said rotating is accomplished by an independent drive operatively coupled with the wave rotor.

3. The method of claim 1, wherein said retaining facilitates balancing of the fluid flow into and out of the passageway.

4. The method of claim 1, wherein the wave rotor having a plurality of passageways, and which further includes repeating acts (a)-(i) for each of said plurality of passageways.

5. The method of claim 1, wherein said burning is defined by a detonative combustion process;

wherein said wave rotor rotates in a first direction; and

wherein said routing is in the direction of the rotation of the wave rotor.

6. The method of claim 5, wherein said delivering occurring to the first portion of the buffer gas during said routing;

and

wherein said delivering provides the quantity of fuel to only a first part of the first portion of buffer gas and does not provide fuel to a second part of the first portion of the buffer gas.

7. The method of claim 1, wherein said rotating includes a start up phase and during the start up phase at least a portion of said rotating is accomplished through an independent drive operatively coupled with the wave rotor;

wherein the rotor includes a plurality of passageways, and acts (a)-(i) are repeated for each of said plurality of passageways;

wherein said rotating is in a first direction;

wherein said rotating is in the first direction; and

wherein said burning is defined by a detonative combustion process within each of the plurality of passageways.

8. The method of claim 7, wherein said delivering occurring to the first portion of the buffer gas during said routing, and said delivering introduces the quantity of fuel to only a first part of the first portion of the buffer gas and a second part of the first portion of the buffer gas does not have fuel introduced therein by said delivering.