David M Sweet

US Patent:

20110173988, Jul 21, 2011

Filed:

Nov 13, 2008

Appl. No.:

13/121209

Inventors:

David H. Sweet - Jupiter FL, US
Stephen H. Silder - Palm City FL, US

International Classification:

F02C 9/28

US Classification:

60773, 60793, 60 39281

Abstract:

A gas turbine engine control system includes a module operable to fail-fix the gas turbine engine to one of a multiple of pre-determined modes in response to failure of an automatic control.

US Patent:

20120310448, Dec 6, 2012

Filed:

Jun 3, 2011

Appl. No.:

13/152430

Inventors:

David H. Sweet - Jupiter FL, US

Assignee:

SIKORSKY AIRCRAFT CORPORATION - Stratford CT

International Classification:

B64D 31/06

US Classification:

701 3

Abstract:

A method of aircraft engine thermal threat mitigation includes detecting an airflow thermal profile at a location on the aircraft forward of an aircraft engine inlet and transmitting the thermal profile to an aircraft control system. The thermal profile is compared to a catalog of thermal threat profiles at the aircraft control system and a determination is made if a thermal threat is present based on the comparison. A thermal threat mitigation measure is initiated to reduce an effect of the thermal threat on aircraft engine performance.

US Patent:

50203169, Jun 4, 1991

Filed:

May 19, 1989

Appl. No.:

7/354534

Inventors:

David H. Sweet - Tequesta FL
Charles E. Greenberg - Jupiter FL
Nicholas D. Lappos - Orange CT
David M. Walsh - Jupiter FL
Richard P. Meisner - Glastonbury CT

Assignee:

Coltec Industries Inc. - West Hartford CT

International Classification:

F02C 928

US Classification:

60 39282

Abstract:

The speed 54,56 of the free turbine 40 of a helicopter engine 22 is compared 134,138 with the speed 142,140 of the helicopter rotor 10 to indicate 106,108 a specific magnitude of autorotation and the deceleration 150 of the rotor above either one of two threshold magnitudes 220,222 (dependent on the magnitude of autorotation) is utilized 81,68,69 to increase fuel flow 72 to the engine according to a specific schedule 160,162 determined by the type of autorotation, in anticipation of rotor speed droop which would otherwise occur during recovery from the autorotation maneuver.

US Patent:

53137787, May 24, 1994

Filed:

Dec 10, 1992

Appl. No.:

7/988520

Inventors:

David H. Sweet - Tequesta FL
Charles W. Evans - Norfolk CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 918

US Classification:

60 3902

Abstract:

A bleed air control system for an aircraft gas turbine engine operates in a fuel saving mode in response to operation of the aircraft in a steady-state cruise condition (215,350) within a threshold flight envelope (202,310) during steady-state engine operation above a threshold range. During operation in the fuel saving mode, a gas turbine engine compressor bleed valve (10) is closed. The rate of bleed valve closure is determined as a function of bleed valve position (12,20) and gas generator speed (26,30) at the instant the fuel savings mode is initiated. The bleed air control system is returned to normal operation in response to actual or commanded engine acceleration above respective threshold magnitudes, in response to aircraft load factor differing from a reference load factor by a threshold magnitude, and in response to the discontinued operation of the aircraft at steady-state cruise conditions, discontinued steady-state operation of the engine above the transient range, or operation of the aircraft outside of the threshold flight envelope.

US Patent:

49982028, Mar 5, 1991

Filed:

May 19, 1989

Appl. No.:

7/354533

Inventors:

David M. Walsh - Jupiter FL
Charles E. Greenberg - Jupiter FL
Nicholas D. Lappos - Orange CT
David H. Sweet - Tequesta FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 908

US Classification:

364431020

Abstract:

A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down (120, 103-105).

US Patent:

20150225088, Aug 13, 2015

Filed:

Feb 10, 2015

Appl. No.:

14/618095

Inventors:

- Stratford CT, US
David H. Sweet - Jupiter FL, US

International Classification:

B64D 31/06
F02D 41/10
F02D 41/02

Abstract:

A method of adaptive engine acceleration for accessory loads includes receiving an accessory load indicator corresponding to an accessory load of an engine. The accessory load indicator is compared to an adjustment threshold. An acceleration rate of the engine is increased based on determining that the accessory load indicator is below the adjustment threshold. The acceleration rate of the engine is decreased based on determining that the accessory load indicator is above the adjustment threshold.