HUGH GLENN EVANS
Pilots at 27 Ave, Spokane, WA

4483147, Nov 20, 1984

Apr 27, 1981

6/257864

Hugh G. Evans - Spokane WA
Stephen Speer - Spokane WA
James A. Christy - Spokane WA

F02B 3712

60611

In combination with an internal combustion engine and an air compressor, for use in an aircraft, the compressor providing compressed air to the engine's air inlet, there is provided a variable overboard bleed valve. The bleed valve is operated by a valve controller which controls the position of the bleed valve in response to changes in engine operating conditions. This permits maintaining optimum compressor operation over a wide range of engine operating conditions without exceeding the critical pressure of the compressor, so as to avoid surge. The controller can be preferably linked to the propeller governor and the throttle control for the aircraft, so as to move in response to movement of the governor and throttle control.

4469078, Sep 4, 1984

Jul 10, 1981

6/281944

Stephen R. Speer - Spokane WA
Hugh G. Evans - Spokane WA
James S. Christy - Spokane WA

F02B 3712

123564

In combination with an internal combustion engine and an air compressor, for use in an aircraft, the compressor providing compressed air to the engine's air inlet, there is provided a variable overboard bleed valve. The bleed valve is operated by a valve controller which controls the position of the bleed valve in response to changes in engine operating conditions. This permits maintaining optimum compressor operation over a wide range of engine operating conditions without exceeding the critical pressure of the compressor, so as to avoid surge. The controller can be preferably linked to the propeller governor and the throttle control for the aircraft, so as to move in response to combined movement of the governor and throttle control. The combined movement can be obtained using a pair of cables connected to a pivoting plate connected to the rotating control shaft of a butterfly valve.

4424781, Jan 10, 1984

Jul 22, 1982

6/400899

Stephen R. Speer - Spokane WA
Hugh G. Evans - Spokane WA

F02D 908

123342

A control linkage is provided between an actuating crank and the throttle butterfly valve of an internal combustion engine. The control linkage is a second degree hesitation mechanism, such as an epicyclic gear train, for example having a gear ratio of 4:1 and an eccentricity ratio of between 0. 7 and 0. 8. The control linkage results in a more linear relationship between engine output and the rotational movement of the actuating crank.

4428550, Jan 31, 1984

Oct 21, 1981

6/313470

Hugh G. Evans - Spokane WA
Stephen Speer - Spokane WA
James S. Christy - Spokane WA

B64C 1704

244 93

A conventional aircraft having horizontal stabilizers and hinged elevators, which is controlled, preferably, through push-pull rods, is provided with a dynamic torque (bob) weight connected to a rotating member, in the direct line of control to the elevator surfaces. The torque member is located in the nose portion of the aircraft with its center of gravity angled up from 20. degree. to 50. degree. when the elevator surfaces are in the neutral position. The torque member is also mounted in a flexible manner to isolate it from horizontal tail vibrations, or flutter.

4399665, Aug 23, 1983

Dec 7, 1981

6/327813

Hugh G. Evans - Spokane WA
Stephen Speer - Spokane WA
James S. Christy - Spokane WA
Stanley S. Lafrenz - Sandpoint ID

B60M 304

62239

An air conditioning system for powered aircraft is provided wherein a refrigerant compressor is located immediately adjacent to the alternator at the right forward portion of a horizontally opposed aircraft engine. The compressor is mechanically driven indirectly from the main bulkhead/starter ring gear assembly through a twin sheaved pulley on the alternator. The air conditioning system also is provided with two sets of inlet ports for cooling air flow to a refrigerant condenser. One set of inlet ports accepts ram air when the aircraft is airborne. The second set of ports is closable and accepts air when an interior intake impeller is activated. The engine-compressor-alternator combination fits within an aerodynamic cowling having no greater frontal area than one required for the engine without the compressor.

5076220, Dec 31, 1991

Jul 25, 1989

7/390896

Hugh G. Evans - Spokane WA
Stephen Speer - Spokane WA

F02B 7506

123 65VC

In an internal combustion engine wherein the air inlet ports are opened and closed directly by the reciprocating movement of the piston, the crankshaft is laterally offset from the central plane common to the longitudinal axes of all of the cylinders. This results in a substantial increase in the power output of the engine.