The Installation, Testing and Lessons Learned of the TF40B Gas Turbine Test Facility

1995 ◽  
Author(s):  
Jeffrey S. Patterson ◽  
Howard Harris
Keyword(s):  
Gas Turbine ◽  
Lessons Learned ◽  
Cold Weather ◽  
Test Facility ◽  
Control Panel ◽  
Foreign Object Damage ◽  
Test Engine ◽  
On Line ◽  
Air Cushion ◽  
Naval Surface Warfare

The TF40B Gas Turbine Test Facility is the only dedicated Landing Craft, Air Cushion main propulsion engine test complex available to the U.S. Navy. This facility, located at the Naval Surface Warfare Center, Carderock Division (NSWCCD) in Philadelphia, PA, began operation in August, 1992. Since then, the test engine has logged approximately 230 starts and 350 operating hours. This paper will present the installation, testing and lessons learned of the TF40B test facility. The installation section will discuss the modifications made to the existing test facility to accept the TF40B engine. The test section will include the Foreign Object Damage (FOD) screen evaluation, both on-line and crank wash detergent fluid evaluations, cold weather fuel testing, engine vent line testing and Aerojet 5 oil evaluation. The lessons learned section will include problems related to the electric starter, waterbrake, inlet and exhaust systems, data acquisition system, instrumentation control panel and the test cell equipment arrangement.

The Installation, Testing, and Lessons Learned of the TF40B Gas Turbine Test Facility

1996 ◽  
Vol 118 (2) ◽  
pp. 375-379
Author(s):  
J. S. Patterson ◽  
H. Harris
Keyword(s):  
Gas Turbine ◽  
Lessons Learned ◽  
Cold Weather ◽  
Test Facility ◽  
Control Panel ◽  
Foreign Object Damage ◽  
Test Engine ◽  
On Line ◽  
Air Cushion ◽  
Naval Surface Warfare

The TF40B Gas Turbine Test Facility is the only dedicated Landing Craft, Air Cushion main propulsion engine test complex available to the U.S. Navy. This facility, located at the Naval Surface Warfare Center, Carderock Division (NSWCCD) in Philadelphia, PA, began operation in August, 1992. Since then, the test engine has logged approximately 230 starts and 350 operating hours. This paper will present the installation, testing, and lessons learned of the TF40B test facility. The installation section will discuss the modifications made to the existing test facility to accept the TF40B engine. The test section will include the Foreign Object Damage (FOD) screen evaluation, both on-line and crank wash detergent fluid evaluations, cold weather fuel testing, engine vent line testing and Aerojet 5 oil evaluation. The lessons learned section will include problems related to the electric starter, waterbrake, inlet and exhaust systems, data acquisition system, instrumentation control panel, and the test cell equipment arrangement.

On-Line Detergent Washing: Reducing the Environmental Effects on the LCAC Gas Turbine Engines

1992 ◽  
Author(s):  
Jeffrey S. Patterson ◽  
Soren K. Spring
Keyword(s):  
Gas Turbine ◽  
Systems Engineering ◽  
Present Method ◽  
Engine Performance ◽  
Turbine Engines ◽  
Harsh Environment ◽  
Gas Turbine Engines ◽  
Test Results ◽  
On Line ◽  
Air Cushion

The Landing Craft Air Cushion (LCAC) gas turbine engines operate in an extremely harsh environment and are exposed to excessive amounts of foreign contaminants. The present method of crank washing is effective when properly performed, but is labor intensive and increases craft downtime. Naval Ship Systems Engineering Station (NAVSSES) designed and installed a prototype on-line detergent wash system which reduced maintenance and craft downtime. Initial test results indicated that the system reduced engine performance degradation and corrosion.

Component Tests With a Model V84.3A Gas Turbine in the Siemens Test Facility in Berlin

2002 ◽  
Author(s):  
Christof Lechner ◽  
Bernward Mertens ◽  
Dieter Warnack ◽  
Dirk Weltersbach ◽  
Herwart Ho¨nen
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Field Measurements ◽  
Test Facility ◽  
Prediction System ◽  
Test Bed ◽  
Surge Margin ◽  
Compressor Surge ◽  
On Line ◽  
Flow Duct

In its Gas Turbine Development and Manufacturing Center in Berlin Siemens runs a test bed for gas turbine prototypes. Since the end of 1998, the new model V84.3A gas turbine has been undergoing tests at this facility. One focus of last year’s tests was on flow field measurements with pneumatic probes in the exit flow duct of the turbine at various load levels to characterize the flow in the diffuser and provide a data base. Another item was the further investigation of the compressor surge margin and the validation of a newly-developed on-line surge prediction system.

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.

scholarly journals British Experience Using the Aero Derived Gas Turbine for Main Propulsion in Air Cushion Vehicles and Fast Patrol Craft

1972 ◽  
Author(s):  
M. L. Woodward
Keyword(s):  
Gas Turbine ◽  
Lessons Learned ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Air Cushion ◽  
British Experience ◽  
Air Cushion Vehicle ◽  
Air Cushion Vehicles

The paper outlines the experiences which have resulted from the application of two gas turbine engines (Proteus and Gnome) to provide main propulsion in marine craft. The emphasis is on the use of these engines in the Air Cushion Vehicle (Hovercraft). Summarizing the lessons learned with the Marine Proteus powering fast displacement craft, and the development of the engine for this role, the author then relates this work to the advent of Hovercraft. The fore-running small hovercraft had been largely dependent on the Marine Gnome engine, and much of the experience with both units can be cross-related. Marine Proteus entered the hovercraft world in the larger vehicles. This experience is discussed in some detail, and is further correlated to the continuing build-up of usage of the same engine in Fast Patrol Boats and Hydrofoil Craft.

Rolls Royce/Allison 501-K Gas Turbine: Anti-Fouling Compressor Coatings Shipboard — Phase I

2003 ◽  
Author(s):  
Daniel E. Caguiat ◽  
David M. Zipkin ◽  
Jeffrey S. Patterson
Keyword(s):  
Gas Turbine ◽  
United States Navy ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Time Data ◽  
Turbine Generator ◽  
Turbine Engine ◽  
Test Engine ◽  
Compressor Performance ◽  
Naval Surface Warfare

Naval Surface Warfare Center Carderock Division (NSWCCD) Gas Turbine Emerging Technologies Code 9334 conducted a land-based evaluation of fouling-resistant compressor coatings for the 501-K17 Ship Service Gas Turbine Generator (SSGTG) [1]. The purpose of this evaluation was to determine whether such coatings could be used to decrease the rate of compressor fouling and associated fuel consumption. Based upon favorable results from the land-based evaluation, a similar coated compressor gas turbine engine was installed onboard a United States Navy vessel. Two data acquisition computer (DAC) systems and additional sensors necessary to monitor and compare both the coated test engine and an uncoated control engine were added. The goal of this shipboard evaluation was to verify land-based results in a shipboard environment. Upon completion of the DAC installation, the two gas turbine engines were operated and initial data was stored. Shipboard data was compared to land-based data to verify validity and initial compressor performance. The shipboard evaluation is scheduled for completion in June 2003, at which time data will be analyzed and results published.

scholarly journals Experience With the TF40B Engine in the LCAC Fleet

1992 ◽  
Author(s):  
Edward M. House
Keyword(s):  
Gas Turbine ◽  
Hot Corrosion ◽  
Compressor Blade ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Improvement Program ◽  
Air Cushion ◽  
Engine Components ◽  
Carbon Erosion ◽  
The U.S

Four Textron Lycoming TF40B marine gas turbine engines are used to power the U.S. Navy’s Landing Craft Air Cushion (LCAC) vehicle. This is the first hovercraft of this configuration to be put in service for the Navy as a landing craft. The TF40B has experienced compressor blade pitting, carbon erosion of the first turbine blade and hot corrosion of the hot section. Many of these problems were reduced by changing the maintenance and operation of the LCAC. A Component Improvement Program (CIP) is currently investigating compressor and hot section coatings better suited for operation in a harsh marine environment. This program will also improve the performance of some engine components such as the bleed manifold and bearing seals.

Computational investigation of foreign object damage sustained by environmental barrier coatings (EBCs) and SiC/SiC ceramic-matrix composites (CMCs)

2015 ◽  
Vol 11 (2) ◽  
pp. 238-272 ◽  
Author(s):  
Mica Grujicic ◽  
Jennifer Snipes ◽  
Ramin Yavari ◽  
S. Ramaswami ◽  
Rohan Galgalikar
Keyword(s):  
Gas Turbine ◽  
Ceramic Matrix ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Foreign Object ◽  
Barrier Coatings ◽  
Content Type ◽  
Environmental Barrier Coatings ◽  
Foreign Object Damage ◽  
Environmental Barrier

Purpose – The purpose of this paper is to prevent their recession caused through chemical reaction with high-temperature water vapor, SiC-fiber/SiC-matrix ceramic-matrix composite (CMC) components used in gas-turbine engines are commonly protected with so-called environmental barrier coatings (EBCs). EBCs typically consist of three layers: a top thermal and mechanical protection coat; an intermediate layer which provides environmental protection; and a bond coat which assures good EBC/CMC adhesion. The materials used in different layers and their thicknesses are selected in such a way that the coating performance is optimized for the gas-turbine component in question. Design/methodology/approach – Gas-turbine engines, while in service, often tend to ingest various foreign objects of different sizes. Such objects, entrained within the gas flow, can be accelerated to velocities as high as 600 m/s and, on impact, cause substantial damage to the EBC and SiC/SiC CMC substrate, compromising the component integrity and service life. The problem of foreign object damage (FOD) is addressed in the present work computationally using a series of transient non-linear dynamics finite-element analyses. Before such analyses could be conducted, a major effort had to be invested toward developing, parameterizing and validating the constitutive models for all attendant materials. Findings – The computed FOD results are compared with their experimental counterparts in order to validate the numerical methodology employed. Originality/value – To the authors’ knowledge, the present work is the first reported study dealing with the computational analysis of the FOD sustained by CMCs protected with EBCs.

Experimental Study of Combustion on a Micro Gas Turbine Combustor

2008 ◽  
Author(s):  
Feng-Shan Wang ◽  
Wen-Jun Kong ◽  
Bao-Rui Wang
Keyword(s):  
Gas Turbine ◽  
Pressure Loss ◽  
Loss Factor ◽  
Total Pressure ◽  
Combustion Efficiency ◽  
Total Pressure Loss ◽  
Test Facility ◽  
Inlet Temperature ◽  
Micro Gas Turbine ◽  
Oil Fuel

A research program is in development in China as a demonstrator of combined cooling, heating and power system (CCHP). In this program, a micro gas turbine with net electrical output around 100kW is designed and developed. The combustor is designed for natural gas operation and oil fuel operation, respectively. In this paper, a prototype can combustor for the oil fuel was studied by the experiments. In this paper, the combustor was tested using the ambient pressure combustor test facility. The sensors were equipped to measure the combustion performance; the exhaust gas was sampled and analyzed by a gas analyzer device. From the tests and experiments, combustion efficiency, pattern factor at the exit, the surface temperature profile of the outer liner wall, the total pressure loss factor of the combustion chamber with and without burning, and the pollutants emission fraction at the combustor exit were obtained. It is also found that with increasing of the inlet temperature, the combustion efficiency and the total pressure loss factor increased, while the exit pattern factor coefficient reduced. The emissions of CO and unburned hydrogen carbon (UHC) significantly reduced, but the emission of NOx significantly increased.

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