Enhanced TF40B Gas Turbine Engine Bleed Air Anti-Ice System (BAAS) Development

2004 ◽  
Author(s):  
Roger Yee ◽  
Lee Myers
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Lessons Learned ◽  
Life Extension ◽  
Cold Weather ◽  
Development Effort ◽  
Engine Control ◽  
Turbine Engine ◽  
Service Life Extension

The Landing Craft Air Cushion (LCAC) Service Life Extension Program (SLEP) upgrades the current TF40B gas turbine engine and analog control system to an Enhanced TF40B (ETF40B) gas turbine with a Full Authority Digital Engine Control (FADEC) system. This upgrade and enhancement will provide additional engine horsepower, increased engine reliability, modern digital engine control equipment, and a Bleed Air Anti-Ice System (BAAS) for the LCAC during cold weather operations. The original permanent BAAS system for the SLEP configured LCAC has been redesigned as a “removable kit” to reduce overall craft weight and to minimize maintenance for the crews. The development has been an ongoing effort between the Navy, Textron Marine & Land Systems who is the LCAC craft builder, and Vericor Power Systems, who is the ETF40B manufacturer. This paper will document and outline the BAAS development effort and the many lessons learned during the design of a prototype BAAS system for the ETF40B engine.

Development of the Full Authority Digital Engine Control (FADEC) System for the Enhanced TF40B Gas Turbine Engine on the U.S. Navy’s Landing Craft, Air Cushion (LCAC) Vehicles

2005 ◽  
Author(s):  
Lance Shappell ◽  
Lee Myers ◽  
Roger Yee
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Lessons Learned ◽  
Life Extension ◽  
Development Effort ◽  
Engine Control ◽  
Turbine Engine ◽  
Analog Control ◽  
Service Life Extension ◽  
Air Cushion

The Landing Craft Air Cushion (LCAC) Service Life Extension Program (SLEP) upgrades the current main propulsion engine and analog control system to the Enhanced TF40B (ETF40B) gas turbine configuration with a Full Authority Digital Engine Control (FADEC) system. The FADEC system is an integral part of the ETF40B gas turbine configuration and interfaces with the new LCAC Control and Alarm Monitoring System (CAMS). In addition to increased reliability, the FADEC requires minimal maintenance and can provide uninterrupted engine diagnostic capabilities. The development of the FADEC system has been an ongoing effort among the Navy, Textron Marine & Land Systems (LCAC builder), Vericor Power Systems (ETF40B manufacturer), and Precision Engine Controls Corporation (PECC) (FADEC manufacturer). This paper will outline the FADEC development effort and the lessons learned during the design, environmental qualification, testing and operation for the LCAC.

Enhanced TF40B Gas Turbine Engine Development Program

2002 ◽  
Author(s):  
Roger Yee ◽  
Lee Myers ◽  
Ken Braccio ◽  
Mike Dvornak
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Life Extension ◽  
Engine Control ◽  
Turbine Engine ◽  
Analog Control ◽  
Service Life Extension ◽  
Land Systems ◽  
Engine Development

The Navy Landing Craft Air Cushion (LCAC) Service Life Extension Program (SLEP) upgrades the current TF40B gas turbine engine and analog control system on the LCAC to an Enhanced TF40B (ETF40B) gas turbine with a Full Authority Digital Engine Control (FADEC) system. This upgrade and enhancement will provide additional engine horsepower, increased engine reliability, and modern digital engine control equipment to the LCAC. The success of the ETF40B engine development program has been an ongoing effort between the Navy, the LCAC craft builder Textron Marine & Land Systems (TM&LS), and the engine manufacturer Honeywell Engine and Systems. This paper will document and outline the differences between the TF40B and ETF40B and the efforts of the ETF40B 150 hour endurance qualification test.

DIGATEC (Digital Gas Turbine Engine Control)

1968 ◽  
Author(s):  
J. E. Bayati ◽  
R. M. Frazzini
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Control Mode ◽  
Engine Control ◽  
Analog Simulation ◽  
Turbine Engine ◽  
Engine Control System ◽  
Discharge Temperature ◽  
Basic Operating ◽  
Experimental Runs

The basic operating principles of an electronic digital computer gas turbine engine control system are presented. Closed loop turbine discharge temperature and speed controls have been implemented; their feasibility was demonstrated through hybrid digital/analog simulation and actual tests of a GE J85 turbojet engine through the start mode to maximum afterburner. Control mode description and results of the analysis and experimental runs are given in this paper.

Lightweight fuel pump and metering component for advanced gas turbine engine control

1990 ◽  
Author(s):  
MARK OVERSTREET ◽  
STEVEN ZAKEM ◽  
ROBERT TORNABENE ◽  
JOE BENNETT ◽  
CHARLES TEAGUE
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Control ◽  
Fuel Pump ◽  
Turbine Engine

Low Emission Variable Area Combustor for Vehicular Gas Turbines

1973 ◽  
Vol 95 (3) ◽  
pp. 191-198 ◽  
Author(s):  
D. J. White ◽  
P. B. Roberts ◽  
W. A. Compton
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Environmental Protection Agency ◽  
Gas Turbines ◽  
Gas Turbine Engine ◽  
Protection Agency ◽  
Engine Emissions ◽  
Turbine Engine ◽  
Automotive Engine ◽  
Low Emission

In recent years automotive engine emissions have become subject to stringent Federal legislation. The most severe of these regulations pertains to the 1976 Emission Standards as defined by the Advanced Automotive Power Systems (AAPS) Division of the Environmental Protection Agency (EPA). A unique combustor concept has been developed by Solar which has demonstrated the feasibility of meeting these emission requirements. The integrated emissions of a typical regenerative gas turbine engine employing this combustor type were each below one half of the levels specified by the Federal 1976 Standards, when tested over a simulated federal driving cycle. The success of the feasibility tests for this combustor concept has lead to more fundamental studies and the planned development of a prototype combustor for demonstration on the EPA-AAPS baseline gas turbine engine. The prototype combustor for the baseline engine is described together with its variable area port mechanisms, which has been demonstrated as necessary for emission control.

Development of Small-sized Gas Turbine Engine Control System for Power Generation

2011 ◽  
Vol 14 (4) ◽  
pp. 52-56
Author(s):  
Seong-Jin Hong ◽  
Seung-Min Kim ◽  
Sim-Kyun Yook ◽  
Sam-Sik Nam
Keyword(s):  
Power Generation ◽  
Control System ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Control ◽  
Turbine Engine ◽  
Engine Control System
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