scholarly journals Status of Marine Gas Turbine Inlet Development Program

1979 ◽  
Author(s):  
C. T. Frazier ◽  
R. E. Ruskin ◽  
E. W. Mihalek
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Development Program ◽  
Engine Performance ◽  
Test Procedures ◽  
Inlet System ◽  
Turbine Inlet ◽  
Work Tasks ◽  
The U.S ◽  
Inlet Duct

Over ocean, salt aerosols ingested in the combustion air of a marine gas turbine cause engine compressor fouling and are a primary factor in engine hot section corrosion. To minimize salt ingestion effects on engine performance and life, a high performance salt filtration system is required. The U.S. Navy is currently conducting the Gas Turbine Inlet Development Program. The program consists of work elements including salt filter tests, at-sea salt-in-air measurements, ship aerodynamic studies, inlet duct design, etc. To complete the assigned work tasks, Navy facilities had to develop state-of-the-art instrumentation and test procedures. Based on these work tasks, the U.S. Navy will publish a Gas Turbine Inlet System Design Handbook. The handbook will provide design guidance for the ship builder and inlet duct designer for optimizing shipboard salt filtration perfmance.

The Marine Environment and Its Influence on Inlet System Design

1984 ◽  
Vol 106 (4) ◽  
pp. 819-824 ◽  
Author(s):  
L. V. Shelton ◽  
R. S. Carleton
Keyword(s):  
System Design ◽  
Gas Turbine ◽  
Marine Environment ◽  
Marine Atmosphere ◽  
System Configuration ◽  
Inlet System ◽  
Air Inlet ◽  
Turbine Inlet ◽  
Work Done ◽  
The U.S

Historically, two of the principal hindrances to the design of effective marine gas turbine inlet systems have been the inability to define the marine environment and to identify the influence of this environment on the inlet system configuration. This paper summarizes the work done by the U.S. Navy to qualitatively and quantitatively define the composition of the marine atmosphere and identify inlet system design practices that can be employed to assist in designing an effective combustion air inlet system.

scholarly journals Low-Cost Small Gas Turbine

1974 ◽  
Author(s):  
A. M. Heitmann ◽  
J. W. Rizika
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Low Cost ◽  
Development Program ◽  
Engine Performance ◽  
Manufacturing Cost ◽  
Frame Size ◽  
Turbine Engine ◽  
The Core ◽  
Engine Concept

This paper presents information on the NREC core engine development program. The subject engine is a 100-hp, two-shaft gas turbine that is the low-power end of a family of engines up to 500 hp, both nonregenerative and regenerative. The major goal of the program has been the development of a low-cost small gas turbine engine (less than $5/hp to produce in quantities of 15,000/yr). Other objectives include low emissions (meeting the anticipated EPA standards for the markets of interest), relatively high performance (design point SFC = 0.7 for the simple-cycle engine and 0.4 for the regenerative version), and relatively long life (10,000-hr life at design power and a minimum service period of 500 hr). Items specifically covered in this paper include the following: (a) A description of the core engine concept. Frame size, regenerative, recuperative, and air compressor versions are discussed. (b) A technical description of the core engine concept. The salient low-cost features are identified. (c) The development program results. Some of the engine performance and manufacturing cost analysis results are given.

Future Vehicular Recuperator Technology Projections

1994 ◽  
Author(s):  
Robert A. Wilson ◽  
Daniel B. Kupratis ◽  
Satyanarayana Kodali
Keyword(s):  
Gas Turbine ◽  
Fuel Economy ◽  
Department Of Defense ◽  
Gas Turbines ◽  
High Performance ◽  
Development Program ◽  
Turn Of The Century ◽  
Turbine Engine ◽  
Technology Roadmap ◽  
Vehicle Propulsion

The Department of Defense and NASA have funded a major gas turbine development program, Integrated High Performance Turbine Engine Technology (IHPTET), to double the power density and fuel economy of gas turbines by the turn of the century. Seven major US gas turbine developers participated in this program. While the focus of IHPTET activity has been aircraft propulsion, the same underlying technology can be applied to water craft and terrestrial vehicle propulsion applications, such as the future main battle tank. For these applications, the gas turbines must be equipped with recuperators. Currently, there is no technology roadmap or set of goals to guide industry and government in the development of a next generation recuperator for such applications.

Numerical Analysis of Gas Turbine Inlet Fogging Nozzle Manifold Pressure Drop

2014 ◽  
Author(s):  
Hai Zhang ◽  
Qun Zheng ◽  
Mustapha Chaker ◽  
Cyrus Meher-Homji
Keyword(s):  
Pressure Drop ◽  
Gas Turbine ◽  
Flow Resistance ◽  
Research Effort ◽  
Water Injection ◽  
Injection Velocity ◽  
Injection Angle ◽  
Turbine Inlet ◽  
Area Of Concern ◽  
Inlet Duct

The air pressure drop over the nozzles manifolds of inlet fogging system and the flow resistance downstream of the nozzle array (manifold) have always been an area of concern and is the object of this paper. Fogging nozzles arrays (involving several hundred nozzles) are mounted on channels and beams, downstream of the inlet filters and affect the pressure drop. The water injection angle, nozzle injection velocities and the progressive evaporation of the water droplets evaporation all influence the inlet pressure seen at the gas turbine inlet. This paper focuses on a numerical simulation investigation of flow resistance (pressure drop) of inlet fogging systems. In this research effort, the inlet duct is meshed in order to compute the pressure drop over the nozzles frames in fogging and non-fogging conditions. First, the resistance coefficients of an air intake filter are obtained by numerical and experimental methods, and then the coefficients are used for the simulation of the inlet duct by considering the filter as a porous media. Effects of nozzle spread pattern and water injection pattern are then modeled. The results indicate that injection velocity and arrangement of nozzles could have significant effects on the pressure drop and intake distortion, which will affect compressor performance. This paper provides a comprehensive analysis of the pressure drop and evaporation of inlet fogging and will be of value to gas turbine inlet fogging system designers and users.

Development of Rigid Inflatable Boats for U.S. Navy Shipboard Use

1985 ◽  
Vol 22 (03) ◽  
pp. 211-218
Author(s):  
David W. Amick ◽  
Robert Hamilton ◽  
Curtis E. Shields
Keyword(s):  
High Performance ◽  
Surf Zone ◽  
Single Point ◽  
Development Program ◽  
Feasibility Studies ◽  
Breaking Waves ◽  
Coast Guard ◽  
Superior Performance ◽  
Concept Evaluation ◽  
The U.S

The Rigid Inflatable Boat (RIB) was originally developed as a gasoline outboard powered craft for surf zone rescue use by the Royal National Lifeboat Institution in the United Kingdom. The objectives were to provide a craft with extremely good stability characteristics to operate in steep onshore breaking waves without capsizing, and to improve the safety of operations alongside other vessels. Open ocean rescue and boarding applications were of interest to the U.S. Coast Guard because of the inherent stability and alongside safety of the RIB. Subsequent feasibility studies by the U.S. Navy indicated that the RIB would be superior in performance to the present 26-ft motor whaleboat, and could also reduce topside weight. The Navy opted for diesel inboard power for the RIB's designated to be carried aboard combatant ships. A diesel-powered RIB was procured for concept evaluation by the U.S. Navy, and has undergone a series of trials and tests to establish smooth-and rough-water performance characteristics. The data acquired confirmed the theoretical performance predicted during the feasibility studies. This first RIB was deployed on a U.S. Navy DDG-993 Class ship utilizing an existing single-point davit. During that deployment, the RIB was launched and retrieved successfully at ship's speeds up to 12 knots. Early indications are that this development program will result in a new ship's boat and an accompanying davit system which will provide the Fleet with a safe, high-performance craft which will greatly enhance operational capability and safety, and substantially reduce topside weight. The enthusiasm of test and Fleet personnel who have operated the RIB attests to its superior performance and to a high degree of probability for success of the program.

The Heat Transfer Performance of Porous Gas Turbine Blades

1968 ◽  
Vol 72 (696) ◽  
pp. 1087-1094 ◽  
Author(s):  
F. J. Bayley ◽  
A. B. Turner
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Engine Performance ◽  
Operating Conditions ◽  
Maximum Temperature ◽  
Specific Power ◽  
Working Fluid ◽  
Inlet Temperature ◽  
Turbine Inlet ◽  
Compression And Expansion

It is well known that the performance of the practical gas turbine cycle, in which compression and expansion are non-isentropic, is critically dependent upon the maximum temperature of the working fluid. In engines in which shaft-power is produced the thermal efficiency and the specific power output rise steadily as the turbine inlet temperature is increased. In jet engines, in which the gas turbine has so far found its greatest success, similar advantages of high temperature operation accrue, more particularly as aircraft speeds increase to utilise the higher resultant jet velocities. Even in high by-pass ratio engines, designed specifically to reduce jet efflux velocities for application to lower speed aircraft, overall engine performance responds very favourably to increased turbine inlet temperatures, in which, moreover, these more severe operating conditions apply continuously during flight, and not only at maximum power as with more conventional cycles.

1000 Hour Qualification Test of the Textron Lycoming TF40B Marine Gas Turbine Engine for the U.S. Navy LCAC Craft

1988 ◽  
Author(s):  
Michael J. Zoccoli
Keyword(s):  
Gas Turbine ◽  
High Power ◽  
Duty Cycle ◽  
Development Program ◽  
Continuous Operation ◽  
Qualification Test ◽  
Turbine Engine ◽  
Qualification Testing ◽  
Carbon Erosion ◽  
The U.S

This paper describes the qualification testing of the TF40B marine gas turbine in accordance with the duty cycle as specified in MIL-E-17341C, but with modifications that reflect the specific engine application to the U.S. Navy LCAC vehicle. Among the particular requirements of the 1000 hour test are continuous operation in a salt-laden environment of given concentration and humidity, and frequent shutdowns from relatively high power with an ensuing soakback interval. The narrative discusses the method of test, the duty cycle, and the results which were obtained. In an epilogue which focuses on posttest activities, a description is given of the corrective actions taken to resolve certain problems that arose during the course of the test. One such problem, namely the occurrence of carbon erosion upon certain hot section components, was eliminated by modification to the combustor, in a very successful posttest test development program.

U.S. Navy Development of Air Assist Fuel Nozzle System for the 501K Series Gas Turbine Engines

2002 ◽  
Author(s):  
Matthew G. Hoffman ◽  
Richard J. DeCorso ◽  
Dennis M. Russom
Keyword(s):  
Gas Turbine ◽  
Failure Modes ◽  
Development Program ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Engine Operation ◽  
Air Blast ◽  
Blast Design ◽  
Fuel Nozzle ◽  
The U.S

The U.S. Navy has experienced problems with liquid fuel nozzles used on the Rolls Royce (formerly Allison) 501K series marine gas turbine engines. The 501K engines used by the U.S. Navy power Ship Service Gas Turbine Generators (SSGTGs) on a number of destroyer and cruiser class ships. Over roughly the last 25 years, 3 different nozzle designs have been employed, the latest and current nozzle being a piloted air blast design. The primary failure modes of these designs were internal fuel passage coking and external carbon deposits. The current piloted air blast design has a hard time replacement requirement of 1500 hours. This life is considered unacceptable. To improve fuel nozzle life, the Navy and Turbine Fuel Technologies (formerly Delavan) teamed in a fast track program to develop a new fuel nozzle with a target life of 5000 hours and 500 starts. As a result, an air assist/air blast nozzle was developed and delivered in approximately 6 months. In addition to the nozzle itself, a system was developed to provide assist air to the fuel nozzles to help atomize the fuel for better ignition. Nozzle sets and air assist systems have been delivered and tested at the NSWC Philadelphia LBES (Land Based Engineering Site). In addition, nozzle sets have been installed aboard operating ships for in-service evaluations. During the Phase one evaluation (July 2000 to June 2001) aboard USS Porter (DDG 78) a set of nozzles accumulated over 3500 hours of trouble free operation, indicating the target of 5000 hours is achievable. As of this writing these nozzles have in excess of 5700 hours. The improvements in nozzle life provided by the new fuel nozzle design will result in cost savings through out the life cycle of the GTGS. In fact, the evaluation nozzles are already improving engine operation and reliability even before the nozzles’ official fleet introduction. This paper describes the fuel nozzle and air assist system development program and results of OEM, LBES and fleet testing.

Requirements for Gas Turbine Inlet Systems in Russia

2009 ◽  
Author(s):  
Tagir R. Nigmatulin ◽  
Vladimir E. Mikhailov
Keyword(s):  
Power Generation ◽  
Power Plant ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Oil And Gas ◽  
Inlet System ◽  
Climate Zones ◽  
Russian Market ◽  
Turbine Inlet ◽  
Industrial Gas Turbines

Russian power generation, oil and gas businesses are rapidly growing. Installation of new industrial gas turbines is booming to fulfill the demand from economic growth. Russia is a unique country from the annual temperature variation point of view. Some regions may reach up to 100C. One of the biggest challenges for world producers of gas turbines in Russia is the ability to operate products at power plants during cold winters, when ambient temperature might be −60C for a couple of weeks in a row. The reliability and availability of the equipment during the cold season is very critical. Design of inlet systems and filter houses for the Russian market, specifically for northern regions, has a lot of specifics and engineering challenges. Joint Stock Company CKTI is the biggest Russian supplier of air intake systems for industrial gas turbines and axial-flow compressors. In 1969 this enterprise designed and installed the first inlet for the power plant Dagskaya GRES (State Regional Electric Power Plant) with the first 100MW gas-turbine which was designed and manufactured by LMZ. Since the late 1960s CKTI has designed and manufactured inlet systems for the world market and been the main supplier for the Russian market. During the last two years CKTI has designed inlet systems for a broad variety of gas turbine engines ranging from 24MW up to 110MW turbines which are used for power generation and as a mechanical drive for the oil and gas industry. CKTI inlet systems with filtering devices or houses are successfully used in different climate zones including the world’s coldest city Yakutsk and hot Nigeria. CKTI has established CTQs (Critical to quality) and requirements for industrial gas turbine inlet systems which will be installed in Russia in different climate zones for all types of energy installations. The last NPI project of the inlet system, including a nonstandard layout, was done for a small gas-turbine engine which is installed on a railway cart. This arrangement is designed to clean railway lines with the exhaust jet in a quarry during the winter. The design of the inlet system with efficient multistage compressor extraction for deicing, dust and snow resistance has an interesting solution. The detailed description of challenges, weather requirements, calculations, losses, and design methodologies to qualify the system for tough requirements, are described in the paper.

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