An Intermediate Approach to Communcation and Sensor Interfacing Standardization for Marine Gas Turbine Engines

2005 ◽  
Author(s):  
James J. Nicolo ◽  
David M. Zipkin ◽  
John Scharschan
Keyword(s):  
Gas Turbine ◽  
System Architecture ◽  
Digital Controller ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Generator ◽  
Novel Approach ◽  
Technology Upgrade ◽  
And Control

This paper details the on-going effort of NAVSEA Philadelphia to provide a command and control technology upgrade to the Model 139 Gas Turbine Generator Set, while deploying a novel approach to this process using Open System Architecture Condition Based Maintenance (OSA-CBM) archetype. The long-term goal of the process being implemented is to serve as the foundation for a communication and interfacing standardization for the marine gas turbine (GT) community. The topics to be discussed in this essay span from investigation to a proposed design, which includes physical measurement of parameters, sensor-Full Authority Digital Controller (FADC) interfacing, and overall system architecture.

scholarly journals The Methodology of Stochastic Optimization of Parameters and Control Laws for the Aircraft Gas-Turbine Engines Flow Passage Components

1999 ◽  
Author(s):  
I. N. Egorov ◽  
G. V. Kretinin ◽  
S. S. Kostiuk ◽  
I. A. Leshchenko ◽  
U. I. Babi
Keyword(s):  
Stochastic Optimization ◽  
Gas Turbine ◽  
Stochastic Approach ◽  
Turbine Engines ◽  
Problem Solution ◽  
Gas Turbine Engines ◽  
Control Laws ◽  
Flow Passage ◽  
Optimum Solution ◽  
And Control

This paper presents the main theses of stochastic approach to the multimeasure parameters and control laws optimization for the aircraft gas-turbine engines. The methodology allows us to optimize the engines taking into account the technological deflections which inevitably take place in the process of manufacturing of the engine’s components as well as engine’s control deflections. The stochastic optimization is able to find highly robust solutions, stable to inaccuracies in technological processes. The effectiveness of the methodology is shown by example of optimization problem solution to find the control laws for the flow passage controllable elements of the 4-th generation aircraft mixed-flow turbofan engine. The use of information about the existing and advanced production technology levels during the optimization process, including some components manufacturing accuracy, allows us to considerably increase the probability of optimum solution implementation in practice. In real engine there are some components manufacturing deflections as well as control accuracy deflections. It results a certain engine’s performance deviation. An engine optimization classic deterministic approach can not take into account this circumstance, so the probability of an optimum design implementation is too low.

scholarly journals Experimental Deposition of NaCl Particles From Turbulent Flows at Gas Turbine Temperatures

2019 ◽  
Vol 141 (2) ◽  
Author(s):  
Peter R. Forsyth ◽  
David R. H. Gillespie ◽  
Matthew McGilvray
Keyword(s):  
Gas Turbine ◽  
Turbulent Flows ◽  
Size Range ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Horizontal Pipe ◽  
Experimental Campaign ◽  
System Temperature ◽  
Secondary Air

The ingestion and deposition of solid particulates within gas turbine engines has become a very significant concern for both designers and operators in recent times. Frequently aircraft are operated in environments where sand, ash, dust, and salt are present, which can drive damage mechanisms from long term component degradation to in-flight flame-out. Experiments are presented to assess deposition characteristics of sodium chloride (NaCl) at gas turbine secondary air system temperature conditions in horizontal pipe flow. Monodisperse NaCl particles were generated in the size range 2.0–6.5 µm, with gas temperatures 390–480 °C, and metal temperatures 355–730 °C. Two engine-representative surface roughnesses were assessed. An experimental technique for the measurement of deposited NaCl based on solution conductivity was developed and validated. Experiments were carried out under isothermal and nonisothermal/thermophoretic conditions. An initial experimental campaign was conducted under ambient and isothermal conditions; high temperature isothermal results showed good similarity. Under thermophoretic conditions, deposition rates varied by up to several orders of magnitude compared to isothermal rates.

scholarly journals A Software Environment for the Modelling, Simulation and Control of Industrial Gas Turbine Engines

1991 ◽  
Author(s):  
C. Poole ◽  
A. G. Salsi ◽  
F. S. Bhinder ◽  
S. Kumar
Keyword(s):  
Computer Program ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Software Environment ◽  
Turbine Engine ◽  
Simulation And Control ◽  
Industrial Gas Turbine ◽  
And Control ◽  
Modelling Simulation

This paper describes a computer program which has been developed to simulate industrial gas turbine engines to aid the design and application of fuel controllers. It explains the program structure and, as an example, gives the application of the program to the modelling of a simple two shaft industrial gas turbine engine. A brief discussion of the value of the implementation language, C++, is also given.

Preparation, Structure, and Properties of Ni3Al and NiAl Light Powder Alloys for Aerospace

2007 ◽  
Vol 534-536 ◽  
pp. 1585-1588 ◽  
Author(s):  
K.B. Povarova ◽  
O.A. Skachkov
Keyword(s):  
Gas Turbine ◽  
New Technology ◽  
Turbine Engines ◽  
Heat Sources ◽  
Gas Turbine Engines ◽  
Combustion Chambers ◽  
Term Operation ◽  
Heat Resistant ◽  
Turbine Installation

New light super-heat-resistant powder Ni3Al and NiAl-based alloys (of the Ni-Al-Mo-B, Ni-Al-Fe-La, and Ni-Al-Y2O3 systems), as well as a new technology for preparing and processing them have been developed. The density of the alloys was 7.3-7.5 and ~6 g/cm 3, respectively. The Ni3Al sheets were used to prepare shields for combustion chambers in gas-turbine engines by roomtemperature deformation; the shields are intended for the long-term operation at 1100-1200°C and for the short-term use at 1300°C. The activated NiAl powders alloyed with Fe+La were used to produce sintered complex-shape articles, such as combustion stabilizers in a jet unit of combustion chamber of the gas-turbine installation, heat sources, etc. capable of operating at t≤1500°C under low mechanical stresses. At 1100, 1300, and 1500°C, the 100-h strength of the heat-resistant NiAl- (2-7.5) vol. % Y2O3 alloys subjected to directional recrystallization is 70, 35 and ≥10 MPa, respectively. The vanes, in which the length of recrystallized grain is smaller than the vane length by a factor of 1.5-2, were manufactured from these alloys.

Long Term Thermal Stability of Several Gas Turbine Alloys

2005 ◽  
Author(s):  
L. M. Pike ◽  
S. K. Srivastava
Keyword(s):  
Mechanical Properties ◽  
Thermal Stability ◽  
Gas Turbine ◽  
Operating Costs ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Haynes 230 ◽  
One Year ◽  
Thermal Stability Of

Ever increasing demands for lower gas turbine operating costs have led to the need for longer lasting components. This in turn, requires the availability of alloys which are reliable to such long lifetimes. In the mill produced condition, most alloys have desirable microstructures and mechanical properties. However, after exposure to the harsh temperatures found in gas turbine engines, the microstructures of most alloys will begin to change. The effects on the mechanical properties of such microstructural changes can range from mild deterioration to significant degradation. In this paper, the effects of thermal exposures at temperatures from 1200 to 1600°F for durations up to one year on the mechanical properties of three wrought gas turbine alloys will be reported. The alloys will include HAYNES® 188 alloy (Co-Ni-Cr-W), HAYNES 230® alloy (Ni-Cr-W), and HAYNES HR-120® alloy (Fe-Ni-Cr-Nb-N).

Experimental industrial ion-plasma plants MESh-50 and MAP-R for applying protective coatings on transport and power gas turbine components

2021 ◽  
Author(s):  
S.A. Budinovskiy ◽  
A.A. Lyapin ◽  
A.S. Benklyan
Keyword(s):  
Gas Turbine ◽  
Protective Coatings ◽  
Operating Experience ◽  
Plasma Coating ◽  
Vacuum Arc ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Serial Production ◽  
Ion Plasma

The paper considers selected features of the protective ion-plasma coating deposition onto large-sized gas turbine components using vacuum-arc method by means of the MESh-50 and MAP-R pilot plants. The units have been developed based on the long-term operating experience of MAP-1 (MAP-1M) serial production. These plants are widely used in Russian and international aircraft-building complexes enabling all basic ion-plasma technological processes using standard cathodes made of nickel, cobalt, aluminum alloys and pure metals (Cu, Ti, Cr, Zr, etc.). The increased dimensions of the deposition chamber and the simultaneous use of several evaporators with pipe cathodes 180 mm in diameter and 540 mm high make it possible to apply coatings to large-sized components of gas turbine engines and plants, including such complex parts as “blisk” and “blink”.

Systematic Evaluation of U.S. Navy LM2500 Gas Turbine Condition

2002 ◽  
Vol 124 (3) ◽  
pp. 580-585 ◽  
Author(s):  
B. D. Thompson ◽  
B. Wainscott
Keyword(s):  
Gas Turbine ◽  
Systematic Evaluation ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Short Term ◽  
Engine Vibration ◽  
Mechanical Faults ◽  
System Data ◽  
Short And Long Term

From an operational availability stand point, the U.S. Navy is interested in the short term reliability of its ship based LM2500 gas turbine engines. That is the likelihood that an engine will operate successfully through a six-month deployment (usually 1500 to 2000 operational hours). From a maintenance and cost of ownership standpoint both the short-term and long-term reliability are of concern. Long-term reliability is a measure in time (in operating hours) between engine removals. To address these requirements U.S. Navy Fleet support maintenance activities employ a system of tests and evaluations to determine the likelihood that an LM2500 will meet its short and long-term goals. The lowest level inspection is the predeployment inspection, which attempts to identify primarily mechanical faults with the engine. Gas Turbine Bulletin inspections are used to determine if predefined wear out modes exists. Performance evaluations can be performed which determine the ability of the LM2500 and its control system to meet expected power requirements. Lube oil system data can be analyzed to determine if excessive leakage or excessive scavenge temperatures exist. Engine vibration characteristics can be reviewed to identify the source of both synchronous and nonsynchronous vibration and determine if corrective measures need to be taken. This paper will discuss how the lowest level inspections feed the more sophisticated analysis and how these inspections and evaluations work to provide a systematic method of insuring both short and long-term LM2500 reliability.

scholarly journals Current and Future Materials in Advanced Gas Turbine Engines

1994 ◽  
Author(s):  
G. A. Kool
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Metallic Materials ◽  
Temperature Capability ◽  
Higher Temperature ◽  
Strength And Stiffness

Gas turbine engines are constructed of components with excellent strength and stiffness, a minimum density, a high temperature capability for long times, and at affordable cost. Metallic materials are the centrepiece in fulfilling these requirements. Future gas turbine engines will have to have higher thrust-to-weight ratios, better fuel efficiencies and still lower costs. This will require new and advanced lightweight materials with higher temperature capabilities. This paper discusses some of the presently applied materials in the fan, compressor and turbine sections of gas turbines, and reviews the material developments that are occurring and will be necessary for the near and long term futures.

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