Anthony D Martin

US Patent:

41160002, Sep 26, 1978

Filed:

Nov 1, 1976

Appl. No.:

5/737379

Inventors:

Anthony Newman Martin - Simsbury CT
Carl James Buczek - Manchester CT
Robert Joseph Mongeon - East Longmeadow MA

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 118

US Classification:

60242

Abstract:

Apparatus for controlling the position of a parameter setting device of a gas turbine engine is disclosed. Techniques for improving the accuracy of the control system by incorporating an optical circuit for sensing physical parameters, such as linear position, pressure and temperature are developed. A fiber optic cable linking a remote intelligence processing unit with a sensing unit at the controlled device is employed in the preferred embodiment.

US Patent:

49483374, Aug 14, 1990

Filed:

May 1, 1989

Appl. No.:

7/345938

Inventors:

Anthony N. Martin - Simsbury CT
Robert G. Bartle - Glastonbury CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B64C 1144

US Classification:

416 3

Abstract:

Pitch of a blade (12) on an aircraft engine propulsor (14) is determined by employing a shaft (22) and a bevel gear (23) to alter relative circumferential distance between a first set of teeth (25) and a second set of teeth (26). Said teeth (25,26) creates fluctuations in a magnetic field generated by a magnetic poll piece (28a) wherein said fluctuations are converted to a signal (30) by a coil (28) located on a subsequent engine section (8). The time between pulses of the signal (30) is a function of said relative circumferential distance whereby the time between pulses is a function of the pitch of the blade (12).

US Patent:

42966019, Oct 27, 1981

Filed:

Aug 23, 1979

Appl. No.:

6/069142

Inventors:

Anthony N. Martin - Simsbury CT

Assignee:

Otis Elevator Company - Hartford CT

International Classification:

F02C 942

US Classification:

60224

Abstract:

Fuel flow to a gas turbine engine is controlled in response to power lever position and CDP by a hydromechanical section. The hydromechanical section includes a torque motor which may be activated to modify the fuel flow to the engine in response to a control signal produced by an electronic control section. The electronic control section senses a number of engine and ambient parameters and generates engine operating limits from these parameters. The limit corresponding to the lowest maximum engine speed is selected and referenced to actual engine speed for generating the control signal, thereby providing a closed loop engine speed control. At least one of the computed limits is an actual maximum engine speed for steady state engine operation and is used to recompute the engine scheduled speed so that the actual maximum engine speed is obtained at the maximum power lever advance position; in this way power lever dead band is eliminated. The electronic control also modifies fuel flow to the engine for speed synchronization with another identically controlled engine.

US Patent:

46008705, Jul 15, 1986

Filed:

Nov 17, 1983

Appl. No.:

6/552898

Inventors:

Anthony N. Martin - Simsbury CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

G05B 1142

US Classification:

318610

Abstract:

A position control system having dual controllers, each capable of operating in either a proportional or a proportional plus integral gain mode, is normally operated with one controller in the proportional plus integral mode and the other in the proportional mode, each controller contributing its proportionate part of the output position control signal to the position controlled device, and each controller capable of operating alone in the proportional plus integral mode in the event of a failure.

US Patent:

41174607, Sep 26, 1978

Filed:

Nov 1, 1976

Appl. No.:

5/737380

Inventors:

Kirk Sumner Walworth - Tolland CT
Anthony Newman Martin - Simsbury CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

G05B 1118
G08B 500
G09F 900

US Classification:

340190

Abstract:

Apparatus for sensing and transmitting physical intelligence is disclosed. In one embodiment the intelligence is transmittable from the sensing device to a remotely positioned, intelligence processing unit. The apparatus taught has particular applicability to gas turbine engine control systems requiring the encoding and transmission of accurate physical intelligence from a hostile environment to the remotely positioned intelligence processing unit. Techniques employing time sequencing through a fiber optic circuit of the transmitted intelligence to reduce the size, weight and complexity of the apparatus are developed.

US Patent:

40073610, Feb 8, 1977

Filed:

Jun 11, 1975

Appl. No.:

5/586010

Inventors:

Anthony Newman Martin - Simsbury CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

G05B 1300

US Classification:

2351501

Abstract:

A control computer produces a position error signal in accordance with the difference between the desired position of a controlled device and the actual position of the controlled device. The position error signal is amplified and compensated to produce a series of discrete control pulses of controlled but variable duration which regulate a servo actuating system connected to the controlled device so as to reposition the controlled device to the desired position. The servo actuating system is a simple on-off integrating valve which does not depend on feedback or other techniques to regulate the position of the controlled device in response to the control pulses from the control computer. Instead, the gain of the position error signal is varied during each cycle in an adaptive manner as a function of the measured change in position of the controlled device in response to the control pulse during the last previous cycle, and the next control pulse is accordingly generated as a function of the response of the entire control system during that previous cycle.

US Patent:

55450075, Aug 13, 1996

Filed:

Nov 25, 1994

Appl. No.:

8/345653

Inventors:

Anthony N. Martin - Simsbury CT

Assignee:

United Technologies Corp. - Hartford CT

International Classification:

F01D 1122

US Classification:

4151732

Abstract:

The blades and the outer case of an encased engine, such as a turbo engine or the like will expand and contract during periods of operation. Blade expansion and contraction can result from operating temperature changes, rotational velocity changes, or the like. The engine casing includes a segmented seal which is properly spaced apart from the engine blade tips so as to provide optimum operation of the engine. Proximity sensors mounted on the engine detect the radial clearance of the engine blades to the seal segments at all times. The seal segments are mounted on a corrugated piezoelectric support which is electrically stimulated so as to properly adjust the seal segments relative to the blade tips to provide the proper spacing as the blades and case expand and contract. Appropriate stimulation of the piezoelectric support will move the seal segments toward or away from the blade tips as needed.

US Patent:

49348256, Jun 19, 1990

Filed:

Dec 22, 1987

Appl. No.:

7/136798

Inventors:

Anthony N. Martin - Simsbury CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B64C 1150

US Classification:

36443101

Abstract:

Propeller phase control apparatus for use on multi-engine aircraft having, for each engine, an electronic engine control (EEC) for providing an EEC command speed and phase (S/P) signal to control propeller phase and shaft speed, and a speed and phase control (SPC) for regulating the propeller's blade pitch angle to adjust the shaft speed thereof in dependence on the EEC command S/P signal value, includes: a SYNCHROPHASER Reference Unit (SRU) having a signal processor with signal memory, the memory including stored signals definitive of a speed and phase algorithm, the signal processor calculating a common SRU command S/P signal value for all SPCs in accordance with the algorithm and in dependence on the sensed values of selected flight data indicative of engine performance, and further includes an electronic switch for each SPC, for selecting either the SRU command S/P signal of the engine's EEC command S/P signal for presentation to the SPC.

Address:

16 Stuart St, Springfield, MA 01119

VIN:

1G6DP577070108533

Make:

CADILLAC

Model:

CTS

Year:

2007