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 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.

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.

Enhanced TF40B Gas Turbine Engine Design Changes to Improve Resistance to the Landing Craft Air Cushion (LCAC) Operational Environment

2003 ◽  
Author(s):  
Roger Yee ◽  
Lee Myers
Keyword(s):  
Gas Turbine ◽  
Material Selection ◽  
Guide Vane ◽  
The United States ◽  
Life Extension ◽  
Operational Environment ◽  
Guide Vanes ◽  
Service Life Extension ◽  
Air Cushion ◽  
Proper Material

The United States Navy Landing Craft Air Cushion (LCAC) vehicles, under the Service Life Extension Program (SLEP), use the Enhanced TF40B (ETF40B) gas turbine engines for main propulsion and lift. These engines provide the additional engine horsepower needed under high ambient temperature conditions, have an increase in operation reliability, and use modern digital engine control equipment. During craft operations, ETF40B engines are exposed to harsh saltwater and sand environments that will cause severe engine corrosion problems if corrosion resistant design features are not utilized. Proper material selection and utilization of anti-corrosion coatings are extremely important to ensure reliability of ETF40B engines on LCAC. This paper will document and outline the Navy’s efforts to improve the ETF40B engine’s resistance to the LCAC operating environment with a focus on the following components/features: • Carbon and Graphite Free Bushing and Washer Materials for Compressor Guide Vanes; • Coatings between the Compressor Casing and Compressor Guide Vane Bushings; • Use of a Silicone Rubber Abradable Material in the First 4 Stages of the Compressor; • Use of Anti-Corrosion Coatings on all Compressor Guide Vanes and Stems.

Integration of the ETF40B Gas Turbine Engine and FADEC System Into the Landing Craft Air Cushion Vehicle

2000 ◽  
Author(s):  
Howard Harris ◽  
Phil Schneider ◽  
John Richards ◽  
Mike Dvornak
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Field Testing ◽  
Gas Turbine Engine ◽  
Design Development ◽  
Turbine Engine ◽  
Analog Control ◽  
The Us ◽  
Land Systems ◽  
Air Cushion

The US Navy along with Textron Marine & Land Systems (TM&LS) is qualifying and field testing the ETF40B gas turbine engine along with Full Authority Digital Engine Control (FADEC) system as possible upgrades to the current TF40B engine and analog control system currently installed on the Landing Craft Air Cushion (LCAC). The ETF40B engine and FADEC control system are of interest due to: increased power, proposed increase in Mean Time Between Overhauls (MTBO), and proposed increase in engine reliability. The primary topics presented in this paper are: 1. The design, development, and qualification of the ETF40B engine and FADEC control system 2. Integration of the ETF40B engine and FADEC into the LCAC 3. Field test data from two LCACs, follow-up testing and implementation

Optimal State-Space Control of a Gas Turbine Engine

1992 ◽  
Vol 114 (4) ◽  
pp. 763-767 ◽  
Author(s):  
J. W. Watts ◽  
T. E. Dwan ◽  
C. G. Brockus
Keyword(s):  
State Space ◽  
Gas Turbine ◽  
State Space Model ◽  
Gas Turbine Engine ◽  
The State ◽  
Operating Conditions ◽  
Turbine Engine ◽  
Analog Control ◽  
Linear State ◽  
High Level

An analog fuel control for a gas turbine engine was compared with several state-space derived fuel controls. A single-spool, simple cycle gas turbine engine was modeled using ACSL (high level simulation language based on FORTRAN). The model included an analog fuel control representative of existing commercial fuel controls. The ACSL model was stripped of nonessential states to produce an eight-state linear state-space model of the engine. The A, B, and C matrices, derived from rated operating conditions, were used to obtain feedback control gains by the following methods: (1) state feedback; (2) LQR theory; (3) Bellman method; and (4) polygonal search. An off-load transient followed by an on-load transient was run for each of these fuel controls. The transient curves obtained were used to compare the state-space fuel controls with the analog fuel control. The state-space fuel controls did better than the analog control.

Cheng-Cycle Implementation on a Small Gas Turbine Engine

1984 ◽  
Vol 106 (3) ◽  
pp. 699-702 ◽  
Author(s):  
R. Digumarthi ◽  
Chung-Nan Chang
Keyword(s):  
Gas Turbine ◽  
Steam Injection ◽  
Injection System ◽  
Development Effort ◽  
Turbine Engine ◽  
Cycle System ◽  
Experimental Heat ◽  
Continuous Power ◽  
Design And Manufacture ◽  
Gas Turbine Cycle

The Cheng-Cycle turbine engine is a superheated steam injected gas turbine cycle system. This work is based on the Garrett 831 gas turbine. The development effort involved the design and manufacture of an experimental heat recovery steam generator, a steam injection system, and system controls. Measured performance data indicate the 26 percent efficiency improvement has been obtained compared to that of the basic turbine engine at its continuous power rating.

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.

Gas Turbine Power Systems for Military Tracked Vehicles

1983 ◽  
Author(s):  
Geoffrey D. Woodhouse
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Waste Heat ◽  
High Reliability ◽  
Turbine Engines ◽  
Tracked Vehicles ◽  
Turbine Engine ◽  
Response Characteristics ◽  
Air Inlet

The gas turbine engine has been examined as a power plant for military tracked vehicles for over 30 years. Advocates have stressed the potentially high power density and high reliability as factors in favor of the turbine. Several turbine engines have been evaluated experimentally in military tracked vehicles resulting in a better understanding of such aspects as response characteristics and air inlet filtration requirements. Moreover, although the small volume and light weight of aircraft derivative gas turbines have certain virtues, it generally has been concluded that some form of waste heat recuperation is essential to achieve an acceptable level of fuel consumption, despite the increased weight and volume incurred. The selection of the AVCO Lycoming AGT1500 recuperated gas turbine as the power unit for the U.S. Army new M1 “Abrams” main battle tank was a major milestone in the evolution of gas turbine engines for tank propulsion.

Analysis of Indirectly Fired Gas Turbine Power Systems

2007 ◽  
Author(s):  
J. E. Donald Gauthier
Keyword(s):  
Power Generation ◽  
Power Systems ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Turbine Engine ◽  
Engine Design ◽  
Wide Range ◽  
System Configurations

This paper describes the results of modelling the performance of several indirectly fired gas turbine (IFGT) power generation system configurations based on four gas turbine class sizes, namely 5 kW, 50 kW, 5 MW and 100 MW. These class sizes were selected to cover a wide range of installations in residential, commercial, industrial and large utility power generation installations. Because the IFGT configurations modelled consist of a gas turbine engine, one or two recuperators and a furnace; for comparison purpose this study also included simulations of simple cycle and recuperated gas turbine engines. Part-load, synchronous-speed simulations were carried out with generic compressor and turbine maps scaled for each engine design point conditions. The turbine inlet temperature (TIT) was varied from the design specification to a practical value for a metallic high-temperature heat exchanger in an IFGT system. As expected, the results showed that the reduced TIT can have dramatic impact on the power output and thermal efficiency when compared to that in conventional gas turbines. However, the simulations also indicated that several configurations can lead to higher performance, even with the reduced TIT. Although the focus of the study is on evaluation of thermodynamic performance, the implications of varying configurations on cost and durability are also discussed.

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