Teresa C Chin

US Patent:

54655706, Nov 14, 1995

Filed:

Dec 22, 1993

Appl. No.:

8/171786

Inventors:

John C. Szillat - Rockville CT
Nicola Laudadio - Rockville CT
Teresa Chin - Manchester CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 928

US Classification:

60 3906

Abstract:

A fuel control system for a gas turbine engine having a staged combustor includes apparatus and methods to operate the combustor during pilot operation, staged operation, and transition between the two modes of operation. Various construction details are developed which provide a fuel control having a switch with built in hysteresis for determining the transition points between operating modes. In one embodiment, the combustor is switched from pilot to staged operation at a thrust level greater than the thrust level at which the combustor is switched from staged to pilot operation. During transitions between operating modes, the changes in fuel flows are limited by a plurality of rate limits to prevent combustor fuel spikes and blow-outs from occurring. During engine starts, the fuel lines to the main combustor are pre-filled to provide responsiveness during the transition from pilot to staged operation.

US Patent:

55986986, Feb 4, 1997

Filed:

Apr 21, 1995

Appl. No.:

8/426316

Inventors:

John C. Szillat - Rockville CT
Nicola Laudadio - Rockville CT
Teresa Chin - Manchester CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 928

US Classification:

60 3906

Abstract:

A fuel control system for a gas turbine engine having a staged combustor includes apparatus and methods to operate the combustor during pilot operation, staged operation, and transition between the two modes of operation. Various construction details are developed which provide a fuel control having a switch with built in hysteresis for determining the transition points between operating modes. In one embodiment, the combustor is switched from pilot to staged operation at a thrust level greater than the thrust level at which the combustor is switched from staged to pilot operation. During transitions between operating modes, the changes in fuel flows are limited by a plurality of rate limits to prevent combustor fuel spikes and blow-outs from occurring. During engine starts, the fuel lines to the main combustor are pre-filled to provide responsiveness during the transition from pilot to staged operation.

US Patent:

59161264, Jun 29, 1999

Filed:

Apr 21, 1995

Appl. No.:

8/426345

Inventors:

John C. Szillat - Rockville CT
Nicola Laudadio - Rockville CT
Teresa Chin - Manchester CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 726
F02C 926

US Classification:

60 3909

Abstract:

A fuel control system for a gas turbine engine having a staged combustor includes apparatus and methods to operate the combustor during pilot operation, staged operation, and transition between the two modes of operation. Various construction details are developed which provide a fuel control having a switch with built in hysteresis for determining the transition points between operating modes. In one embodiment, the combustor is switched from pilot to staged operation at a thrust level greater than the thrust level at which the combustor is switched from staged to pilot operation. During transitions between operating modes, the changes in fuel flows are limited by a plurality of rate limits to prevent combustor fuel spikes and blow-outs from occurring. During engine starts, the fuel lines to the main combustor are pre-filled to provide responsiveness during the transition from pilot to staged operation.