Donald W Kendrick

US Patent:

6694743, Feb 24, 2004

Filed:

Jul 23, 2002

Appl. No.:

10/200780

Inventors:

Shawn P. Lawlor - Redmond WA
Robert C. Steele - Woodinville WA
Donald Kendrick - Sammamish WA

Assignee:

Ramgen Power Systems, Inc. - Bellevue WA

International Classification:

F02K 710

US Classification:

60772, 60 3934, 60 3935, 60768

Abstract:

A rotary ramjet engine. A rotary ramjet engine is provided operating with a very low axial flow component. The engine has a closely housed rotor and shaft mounted for rotary motion with respect to an engine case. A plurality of ramjet combustors are provided at the periphery of the rotor, and a set of spaced apart helical strakes are provided extending outward from the surface portion of the rotor toward the interior wall of the engine case, less a running clearance therefrom. A centerbody is provided for each ramjet inlet. The centerbody is disposed along a helical axis parallel to the strakes, and includes a leading edge structure, opposing sidewalls, and a shaped cavity, and a rear end wall. Each set of strakes cooperate to define, rearward of the rear end wall of each inlet centerbody, a combustion chamber for mixing therewithin and inlet fluid and burning fuel therein to form hot combustion gases therefrom. A ramjet outlet nozzle structure, including a converging ramjet nozzle throat, and diverging ramjet nozzle are provided for receiving the hot combustion gases and discharging, at a preselected helical angle to the plane of rotation of the rotor, a jet of hot combustion exhaust gases.

US Patent:

6962055, Nov 8, 2005

Filed:

Sep 27, 2002

Appl. No.:

10/260311

Inventors:

Alexander G. Chen - Ellington CT, US
Donald W. Kendrick - Bellevue WA, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C007/228

US Classification:

60746

Abstract:

The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further has different fuel circuits for independently controlling the fuel flow rate for the nozzles in each of the arrays. Each of the nozzles include a fluid channel and one or more swirler vanes in the fluid channel for creating a swirling flow within the fluid channel. A method for injecting a fuel/air mixture into a combustor stage of a gas turbine engine is also described. At least one zone has a flame hot enough to stabilize the entire combustor flame.

US Patent:

7003961, Feb 28, 2006

Filed:

May 5, 2003

Appl. No.:

10/430849

Inventors:

Donald Kendrick - Sammamish WA, US
Shawn P. Lawlor - Redmond WA, US
Robert C. Steele - Woodinville WA, US

Assignee:

Ramgen Power Systems, Inc. - Bellevue WA

International Classification:

F02C 3/00
F23R 3/18
F23R 3/20

US Classification:

60776, 60749, 60750, 60737

Abstract:

A trapped vortex combustor for gas turbine engines. An annular combustor housing is provided having a plurality of inlet centerbodies disposed along a helical axis. The inlet centerbodies include a leading edge structure, opposing sidewalls, a pressurizable cavity, and a rear wall. Inlet centerbodies cooperate with adjacent structure and an aft bluff body to define a trapped vortex cavity combustion chamber for mixing an inlet fluid and burning fuel to form hot combustion gases. Mixing is enhanced by utilizing struts adjacent to the rear wall to create eddies in the fluid flow, and by injecting fuel and/or air in opposition to swirl created by the bulk fluid flow. Hot combustion gases are utilized in a turbine for extraction of kinetic energy, or in heat exchange equipment for recovery of thermal energy. High combustion efficiencies and less than 10 ppm emissions of oxides of nitrogen and of carbon monoxide are achieved.

US Patent:

7011047, Mar 14, 2006

Filed:

Nov 20, 2003

Appl. No.:

10/718730

Inventors:

Michael J. Aarnio - Kirkland WA, US
Donald W. Kendrick - Bellevue WA, US
Thomas R. A. Bussing - Sammamish WA, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F22B 37/48

US Classification:

122379, 122396, 165 95, 134 221

Abstract:

Methods and apparatus are provided for cleaning a surface within a vessel. A fuel/oxidizer charge is provided within a combustion conduit. An initial deflagration commenced in a first portion of the charge produces a final detonation at least in another portion of the charge to expel a shockwave from the conduit which impinges upon the surface. The deflagration-to-detonation transition may be encouraged by mechanical enhancements and/or by making the first charge portion more detonable than the second.

US Patent:

7107772, Sep 19, 2006

Filed:

Jan 31, 2005

Appl. No.:

11/048419

Inventors:

Alexander G. Chen - Ellington CT, US
Donald W. Kendrick - Bellevue WA, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F23R 3/42

US Classification:

60737, 60746

Abstract:

The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further has different fuel circuits for independently controlling the fuel flow rate for the nozzles in each of the arrays. Each of the nozzles include a fluid channel and one or more swirler vanes in the fluid channel for creating a swirling flow within the fluid channel. A method for injecting a fuel/air mixture into a combustor stage of a gas turbine engine is also described. At least one zone has a flame hot enough to stabilize the entire combustor flame.

US Patent:

7509811, Mar 31, 2009

Filed:

Aug 9, 2005

Appl. No.:

11/200333

Inventors:

Alexander G. Chen - Ellington CT, US
Donald W. Kendrick - Bellevue WA, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 7/22
F02C 7/26

US Classification:

60776, 60739, 60746

Abstract:

The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further has different fuel circuits for independently controlling the fuel flow rate for the nozzles in each of the arrays. Each of the nozzles include a fluid channel and one or more swirler vanes in the fluid channel for creating a swirling flow within the fluid channel. A method for injecting a fuel/air mixture into a combustor stage of a gas turbine engine is also described. At least one zone has a flame hot enough to stabilize the entire combustor flame.

US Patent:

8549862, Oct 8, 2013

Filed:

Nov 30, 2009

Appl. No.:

12/627815

Inventors:

Donald W. Kendrick - Bellevue WA, US

Assignee:

Lean Flame, Inc. - Washington DC

International Classification:

F02C 1/00

US Classification:

60772, 60733, 60737, 60750

Abstract:

In one embodiment, a method is provided fuel staging for a trapped vortex (TVC) combustion apparatus comprising an inlet premixer, for injecting fuel-air mixture into the inlet of the combustion apparatus and a vortex premixer, for injecting fuel-air mixture into the recirculating vortex. The combustion apparatus may be part of an engine, such as a gas turbine engine. The method comprises varying the relative proportion of mixture introduced through the inlet and vortex premixers as a function of load.

US Patent:

7267134, Sep 11, 2007

Filed:

Mar 15, 2004

Appl. No.:

10/801215

Inventors:

Michael J. Aarnio - Kirkland WA, US
Donald W. Kendrick - Bellevue WA, US
Thomas R. A. Bussing - Sammamish WA, US
Robert R. Niblock - Kent WA, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B08B 3/12

US Classification:

134166R, 134166 C, 134184, 134186, 122379

Abstract:

A shockwave cleaning apparatus cleans one or more surfaces within a vessel. A sensor senses one or more thermodynamic properties associated with the vessel. A control system is coupled to an initiator and a fuel/oxidizer source to control the firing of the apparatus responsive to input from the sensor.