ROBERT R THOMPSON, JR
Nursing in San Diego, CA

6735951, May 18, 2004

Jan 4, 2002

10/037604

Robert G. Thompson - San Diego CA

Hamilton Sundstrand Corporation - Rockford IL

F02C 600

60774, 60791, 60792

An APU system includes a gas turbine engine having a low pressure spool, a high pressure spool and an electrical generator. The electrical generator is driven by the high pressure spool which is governed to a constant speed. Conversely, the low pressure spool is not governed at all, but is allowed to seek a speed that balances the power developed by the low pressure turbine (LPT) and power absorbed by the low pressure compressor (LPC). A step increase/decrease in electrical power demand is met with a step increase/decrease in fuel flow, which results in an overshoot/undershoot of the new equilibrium turbine inlet temperature TIT. The TIT returns to the new equilibrium when the LP spool has achieved its new shaft speed and new equilibrium power balance. The HP Spool and generator maintain essentially constant speed and frequency, while the LP Spool responds to restore equilibrium. The APUs response to sudden power change is thereby effectively immediate as the power change is decoupled from the large mechanical inertia of the HP and LP spools.

5094082, Mar 10, 1992

Dec 22, 1989

7/455570

Robert G. Thompson - San Diego CA
Colin Rodgers - San Diego CA
Nipulkumar Shah - San Diego CA
Jack R. Shekleton - San Diego CA

Sundstrand Corporation - Rockford IL

F02C 300

60750

In order to provide an expansive central recirculating gas zone (40) in a combustor (10), and in a manner wherein the combustion chamber (20) is of compact volume, a stored energy combustor (10) comprises a vessel (12) having narrow, spaced-apart inlet and outlet ends (14, 16) interconnected by a wall (18) defining a relatively wise combustion chamber (20). The combustion chamber (20) is generally annular and a wall (18) defining the combustion chamber (20) includes an upstream wall region (18a) and a downstream wall region (18c) interconnected by a generally annular side wall region (18b). The inlet end (14) and outlet end (16) are generally tubular extensions of the vessel (12) leading to and from the combustion chamber (20) and oxidant is swirled in the tubular extension (14) leading to the combustion chamber (20) and directed in a swirling annulus into the combustion chamber (20) outwardly of a fuel injector (28). The combustion chamber (20) is formed such that at least the upstream wall region (18a) has an inner surface of gentle radius joining the generally annular side wall region (18b) to the tubular extension (14) of the vessel (12) leading to the combustion chamber (20). With this arrangement, the swirling oxidant annulus expands radially outwardly in a generally conical fashion within the combustion chamber (20) upon exiting the tubular extension (14) while sticking to at least the upstream wall region (18a) of the wall (18) defining the combustion chamber (20).

5491308, Feb 13, 1996

Apr 9, 1992

7/866142

James C. Napier - San Diego CA
Robert G. Thompson - San Diego CA

Sundstrand Corporation - Rockford IL

E04F 1704

181224

In order to reduce noise transmission through the air inlet duct (16) of a turbine engine (10), the air inlet duct (16) provides a non-linear path defined by a bend (24) for air from a source, and the turbine engine (10) includes a sound attenuation assembly (26) in the form of a splitter dissipative silencer disposed near the bend (24) in the air inlet duct (16). More specifically, the turbine engine (10) is such that the splitter dissipative silencer (26) can be formed as a modular assembly (42) removably securable near the bend (24) in the air inlet duct (16) upstream of a radial compressor (12) for removal and/or replacement or availability as an optional component of the turbine engine (10).

6283410, Sep 4, 2001

Nov 4, 1999

9/434054

Robert George Thompson - San Diego CA

Hamilton Sundstrand Corporation - Windsor Locks CT

B64D 2700

244 59

Increased efficiency of operation in pressurized aircraft may be obtained by employing pressurized air to be discharged from an aircraft cabin 10 as combustion air by applying it to the inlet 42 of a cycle compressor 40 whereat it is compressed before being fed to a combustor 52. Fuel from a source 64 is combusted within the combustor 52 and drives a high pressure turbine 48 as well as a low pressure turbine 30, either one of which may drive a load 56, 58 to provide electrical power for the aircraft. In addition, a load compressor 20 provides air to an environmental control system including an ECS turbo machine 88 and a bypass 110 for delivering conditioned air to the cabin 10.

4739899, Apr 26, 1988

Oct 8, 1986

6/916756

Robert W. Thompson - San Diego CA
Angelo V. Pugliese - San Diego CA

UOP Inc. - Des Plaines IL

B65D 5300

220240

A closure assembly for pressure vessels comprising a hollow pressure vessel having an internal cylindrical surface, a cylindrical end plug slidably mounted in the pressure vessel and contacting the internal cylindrical surface, the internal cylindrical surface having a first continuous circular groove to receive a segmented ring which retains the cylindrical end plug in the pressure vessel, and the cylindrical end plug having a second continuous circular groove to receive an O-ring seal, the second continuous circular groove having a ramped bottom and two substantially vertical side walls.

7367193, May 6, 2008

Jul 23, 2003

10/625288

Robert G. Thompson - San Diego CA, US

Hamilton Sundstrand Corporation - Rockford IL

F02C 9/28

60773, 60 39, 60281

An adjustment method and system for an auxiliary power unit (APU) allows the APU speed to vary based on the inlet air temperature to the APU compressor. The APU is controlled by a control law that allows the APU speed to float within a selected range based on speed and electric power generators phase matching criteria that provides smooth power transfer between the APU and a main engine generator. The specific APU mechanical speed for a given temperature may be determined from a compressor map that identifies the optimum combination of pressure ratio, flow rate and efficiency for a given inlet temperature, and avoids running the APU near mechanical resonant vibration conditions.

7117683, Oct 10, 2006

Aug 25, 2004

10/926161

Robert G. Thompson - San Diego CA, US

Hamilton Sundstrand Corporation - Rockford IL

F02C 7/26

60786, 60784

A main engine electric start system for gas turbine propelled aircraft that employs a low-power AC electrical power system to serve as an independent grid to control the functions of induction-type dynamoelectric machines coupled to the main propulsion engines and APU as a starter or generator.

6143718, Nov 7, 2000

Jun 7, 1995

8/483188

Orville G. Kolterman - Poway CA
Robert G. Thompson - San Diego CA
John F. Mullane - Cardiff CA

Amylin Pharmaceuticals, Inc. - San Diego CA

A61K 3810, A61K 3823

514 12

Methods for treating non-insulin-taking Type II diabetes mellitus which comprise administering a therapeutically effective amount of an amylin agonist.