Constant volume combustor having rotating wave rotor

• US 8,555,612 B2
• Filed: 02/21/2012
• Issued: 10/15/2013
• 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:
  US13/401,476
• Publication Number:
  US 20120240585A1
• Time in Patent Office: 602 Days
• Field of Search: 602/47, 607/76, 60/393.4, 60/393.5, 60/393.8, 60/393.9, 60/394.5, 60/397.6, 60/397.8
• 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. The apparatus includes inlet and outlet ports that interface with a plurality of fluid flow passageways on a rotor. A buffer gas is routed through some of the inlet and outlet ports and into and out of the plurality of fluid flow passageways. One of the inlet ports is a buffer gas inlet port that when placed in registry with a fluid flow passageway allows the flow of buffer gas into the respective passageway. Fuel is delivered into the buffer gas proximate the buffer gas inlet port so that only a portion of the buffer gas inlet port receives any fuel. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings.

Claims

1. A method for starting a gas turbine engine, comprising:

(a) providing an engine including a compressor, a combustor including a wave rotor having a plurality of passageways and a turbine;

(b) rotating the wave rotor;

(c) fueling at least a portion of the plurality passageways;

(d) combusting the fuel within the plurality of passageways to form a flow of exhaust gas;

(e) discharging at least a portion of the exhaust gas from the wave rotor and delivering to a bladed rotor within the turbine;

(f) rotating the bladed rotor within the turbine with exhaust gas from said discharging;

(g) repeating acts (a)-(f) to bring the compressor and turbine up to an operating condition;

providing an independent drive operative coupled with the wave rotor; and

wherein at least a portion of said rotating occurring through the independent drive;

which further includes supporting the wave rotor with electromagnetic forces, and wherein the at least a portion of said rotating includes controlling the electromagnetic forces to cause said rotating.

2. The method of claim 1, wherein said repeating continues to start the gas turbine engine.

3. The method of claim 1, wherein said combusting is defined by detonative combustion.

4. A method for starting a gas turbine engine, comprising:

(a) providing an engine including a compressor, a combustor including a wave rotor having a plurality of passageways and a turbine;

(b) rotating the wave rotor;

(c) fueling at least a portion of the plurality passageways;

(d) combusting the fuel within the plurality of passageways to form a flow of exhaust gas;

(e) discharging at least a portion of the exhaust gas from the wave rotor and delivering to a bladed rotor within the turbine;

(f) rotating the bladed rotor within the turbine with exhaust gas from said discharging;

(g) repeating acts (a)-(f) to bring the compressor and turbine up to an operating condition;

providing an independent drive operative coupled with the wave rotor; and

wherein at least a portion of said rotating occurring through the independent drive,

which further includes introducing a working fluid into the combustor, wherein the combustor is a substantially constant volume combustor;

wherein said combustor is defined by detonative combustion;

wherein said at least a portion of said rotating includes a start up portion wherein the wave rotor is driven by the drive;

which further includes providing at least one electromagnetic radial bearing; and

which further includes supporting the wave rotor with the at least one electromagnetic radial bearing.

5. An apparatus, comprising:

a compressor for increasing the pressure of a working fluid passing therethrough, said compressor having a compressor discharge;

a constant volume combustor in fluid communication with said compressor discharge, said constant volume combustor including a rotatable wave rotor and a fuel deliverer, said wave rotor including a plurality of cells for receiving at least a portion of the working fluid from said compressor discharge and a fuel from said fuel deliverer that undergoes combustion within said cells to produce an exhaust gas flow;

a turbine in flow communication with the exhaust fluid flow from said constant volume combustor; and

at least one active electromagnetic radial bearing operable to support said wave rotor.

6. The apparatus of claim 5, wherein the portion of the working fluid and the fuel undergo detonative combustion within said plurality of cells.

7. The apparatus of claim 5, wherein said wave rotor includes a first structure defining the cells and an attachment structure coupled thereto, and wherein said attachment structure engages with said at least one active electromagnetic radial bearing about which said wave rotor rotates, and wherein said first structure is coupled to said attachment structure by pin join means for coupling and thermally isolating said first structure from said at least one active electromagnetic radial bearing.

8. The apparatus of claim 7, which further includes a first end plate and a second end plate for controlling the passage of fluid relative to said plurality of cells, and wherein said rotor has a first end spaced a first gap from said first end plate and an opposite second end spaced a second gap from said second end plate, and wherein said first gap and said second gap are filled with a high pressure working fluid bled from said constant volume combustor.

9. A method for starting a gas turbine engine, comprising:

(a) providing an engine including a compressor, a combustor including a wave rotor having a plurality of passageways and a turbine;

(b) rotating the wave rotor;

(c) fueling at least a portion of the plurality passageways;

(d) combusting the fuel within the plurality of passageways to form a flow of exhaust gas;

(e) discharging at least a portion of the exhaust gas from the wave rotor and delivering to a bladed rotor within the turbine;

(f) rotating the bladed rotor within the turbine with exhaust gas from said discharging;

(g) repeating acts (a)-(f) to bring the compressor and turbine up to an operating condition; and

introducing a working fluid into the combustor, wherein the combustor is a substantially constant volume combustor;

which further includes providing a drive operatively coupled with the wave rotor;

wherein said combustor is defined by detonative combustion;

wherein said rotating includes a start up portion wherein the wave rotor is driven by the drive;

which further includes providing at least one electromagnetic radial bearing; and

which further includes supporting the wave rotor with the at least one electromagnetic radial bearing.