Richard S Dyer

US Patent:

6347509, Feb 19, 2002

Filed:

Jul 15, 1999

Appl. No.:

09/354218

Inventors:

Thomas A. Kaemming - Florissant MO
Paul G. Willhite - Maryland Heights MO
Richard S. Dyer - Maryland Heights MO
Michael A. Guntorius - St. Charles MO

Assignee:

McDonnell Douglas Corporation c/o The Boeing Company - Seattle WA

International Classification:

F02K 500

US Classification:

60248

Abstract:

A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber. The pulsed detonation engine includes a volume of ejector/bypass air surrounding the detonation chamber, which captures the detonation engine exhaust and mixes the exhaust with the ejector air, and a back pressure device for feeding dynamic pressure ejector air to the interior of the detonation chamber near its outlet end.

US Patent:

6446428, Sep 10, 2002

Filed:

Nov 13, 2001

Appl. No.:

10/008799

Inventors:

Thomas A. Kaemming - Florissant MO
Paul G. Willhite - Maryland Heights MO
Richard S. Dyer - Maryland Heights MO
Michael A. Guntorius - St. Charles MO

Assignee:

McDonnell Douglas Corporation - Seattle WA

International Classification:

F02K 700

US Classification:

60247

Abstract:

A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber. The pulsed detonation engine may optionally include a volume of ejector/bypass air surrounding the detonation chamber, which captures the detonation engine exhaust and mixes the exhaust with the ejector air, and a back pressure device for feeding dynamic pressure ejector air to the interior of the detonation chamber near its outlet end.

US Patent:

7637455, Dec 29, 2009

Filed:

Apr 12, 2006

Appl. No.:

11/403252

Inventors:

Joseph S. Silkey - Florissant MO, US
Christopher D. Wilson - St. Louis MO, US
Richard S. Dyer - Maryland Heights MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 33/02

US Classification:

244 53B, 244204, 2442041

Abstract:

An air induction system for an aircraft to control distortion and pressure recovery for improved aerodynamic performance. The system includes an inlet and at least one dielectric barrier discharge generator positioned upstream of the engine for imparting momentum to a low-energy boundary layer of air. A plurality of spaced dielectric barrier discharge generators may be activated in selected combinations to optimize performance at respective flight conditions. In one embodiment, one or more generators may be oriented generally transverse relative to the flow of intake air to eject the boundary layer in a lateral direction and prevent its ingestion by the engine. In another embodiment, one or more generators may be oriented along the direction of flow to accelerate the boundary layer air.

US Patent:

7721989, May 25, 2010

Filed:

Mar 1, 2006

Appl. No.:

11/365900

Inventors:

Richard S Dyer - Maryland Heights MO, US
Thomas A Kaemming - Florissant MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 33/02

US Classification:

244 53B

Abstract:

An inlet for an aircraft, missile or other high speed airborne mobile platform, to receive intake air and compress the intake air for delivery to an engine of the mobile platform. The inlet has an array of inlet elements placed in side-by-side arrangement. Each inlet element has a passage for delivery of intake air. The array provides for compact volume and effective aerodynamic performance. The inlet may be mounted for rotation to start the inlet when at a supersonic speed. The inlet is shorter in length than traditional inlets and can be integrated into a wider variety of airframes, or at locations on existing airframes that would be difficult or impossible to integrate a traditional inlet on.

US Patent:

7975961, Jul 12, 2011

Filed:

Nov 16, 2009

Appl. No.:

12/619028

Inventors:

Joseph S. Silkey - Florissant MO, US
Christopher D. Wilson - St. Louis MO, US
Richard S. Dyer - Maryland Heights MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 33/02

US Classification:

244 53B, 244 53 R, 244204, 2442041

Abstract:

Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the engine. The inlet has a longitudinal axis generally aligned with a direction of flow of the air as the air approaches the inlet. The aircraft also includes at least one first dielectric barrier discharge generator positioned to apply a first force to the air prior to the air being received by the engine. The first force acts in a first direction. The aircraft further includes at least one second dielectric barrier discharge generator positioned to apply a second force to the air prior to the air being received by the engine. The second force acts in a second direction that is non-parallel to the first direction.

US Patent:

8172547, May 8, 2012

Filed:

Jan 31, 2008

Appl. No.:

12/023697

Inventors:

Richard S. Dyer - Maryland Heights MO, US
Joseph S. Silkey - Florissant MO, US
Bradley A. Osborne - Manchester MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

F04B 37/04

US Classification:

417 76, 417158, 417195

Abstract:

A dielectric element barrier discharge pump for accelerating a fluid flow. In one embodiment the pump has a first dielectric layer having a first electrode embedded therein and a second dielectric layer having a second electrode embedded therein. The first and second dielectric layers are further supported apart from one another to form an air gap therebetween. A third electrode is disposed at least partially in the air gap upstream of the first and second electrodes, relative to a direction of flow of the fluid flow. A high voltage supplies a high voltage signal to the third electrode. The electrodes cooperate to generate opposing asymmetric plasma fields in the gap that create an induced air flow within the gap. The induced air flow operates to accelerate the fluid flow as the fluid flow moves through the gap.

US Patent:

8210474, Jul 3, 2012

Filed:

Oct 28, 2008

Appl. No.:

12/259379

Inventors:

Richard S. Dyer - Maryland Heights MO, US
Thomas A. Kaemming - Florissant MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 33/02

US Classification:

244 53B

Abstract:

An inlet for an aircraft, missile or other high speed airborne mobile platform, to receive intake air and compress the intake air for delivery to an engine of the mobile platform. The inlet has an array of inlet elements placed in side-by-side arrangement. Each inlet element has a passage for delivery of intake air. The array provides for compact volume and effective aerodynamic performance. The inlet may be mounted for rotation to start the inlet when at a supersonic speed. The inlet is shorter in length than traditional inlets and can be integrated into a wider variety of airframes, or at locations on existing airframes that would be difficult or impossible to integrate a traditional inlet on.

US Patent:

20020059793, May 23, 2002

Filed:

Nov 13, 2001

Appl. No.:

10/008103

Inventors:

Thomas Kaemming - Florissant MO, US
Paul Willhite - Maryland Heights MO, US
Richard Dyer - Maryland Heights MO, US
Michael Guntorius - St. Charles MO, US

International Classification:

F02K007/02

US Classification:

060/204000, 060/247000

Abstract:

A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber. The pulsed detonation engine may optionally include a volume of ejector/bypass air surrounding the detonation chamber, which captures the detonation engine exhaust and mixes the exhaust with the ejector air, and a back pressure device for feeding dynamic pressure ejector air to the interior of the detonation chamber near its outlet end.