Fuel Flow Elements for Automotive and Small Industrial Gas Turbines

1978 ◽  
Author(s):  
D. K. Andrews ◽  
M. W. Smart
Keyword(s):  
Gas Turbines ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Diverse Range ◽  
Complete Control ◽  
Fuel Flow ◽  
Industrial Gas Turbines ◽  
And Performance ◽  
Type Fuel ◽  
Type Pressure

Requirements are defined for fuel flow control elements to be used with an electronic computer to form a flexible complete control system for a diverse range of small industrial and automotive gas turbine engines. A preferred system configuration is described, suitable for use with a variety of engine types and output powers in the 100 to 1000 kw range and for medium and high quantity production. The solution described uses a gear type fuel pump, a simple metering valve positioned by a moving coil d-c force motor, a diaphragm type pressure drop regulator, and a solenoid high pressure shut-off valve. The reasons for choice of this arrangement and its specific advantages are presented. Development and early service experience with the system are discussed and performance characteristics are presented.

scholarly journals Thermal Spray Manufacturing Issues in Coating IGT Hot Section Components

1997 ◽  
Author(s):  
P. Sahoo ◽  
T. Carr ◽  
R. Martin ◽  
F. Dinh
Keyword(s):  
Gas Turbines ◽  
Protective Coatings ◽  
Turbine Blades ◽  
Shop Floor ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Industrial Gas Turbines ◽  
And Performance ◽  
Thermally Sprayed ◽  
Practical Implications

The desire to improve the performance and efficiency of gas turbine engines has led to higher operating temperatures in the turbine sections of the engine. Present materials and materials under development for hot section turbine blades and vanes are not inherently resistant to hot corrosion, and therefore require protective coatings. In the past two decades this has led to increased use of thermally sprayed MCrAlY coatings, both as stand-alone overlay and as a bond coat for thermal barrier coatings. This paper reviews the issues involved in thermally sprayed MCrAlY and TB coatings onto hot section blades and vanes of industrial gas turbines. The generation of a specification for coating acceptance and its practical implications are discussed. The issues in applying such coatings will be discussed, along with references to manufacturing issues on the shop floor. The difficulties inherent in applying a line-of-sight coating to complex geometric shapes will be discussed, with particular reference to robotics spraying. The utility of using a design-of-experiment approach to satisfy the user will be reviewed. The testing, evaluation, and performance characteristics of typical coatings are discussed.

scholarly journals A Turbine-Speed, Main-Engine Fuel Pump

1971 ◽  
Author(s):  
H. T. Johnson
Keyword(s):  
High Speed ◽  
Turbine Engines ◽  
Engine Fuel ◽  
Gas Turbine Engines ◽  
Fuel Flow Rate ◽  
Fuel Pump ◽  
Fuel Flow ◽  
Turbine Speed ◽  
Main Engine ◽  
Type Fuel

This paper describes the design and experimental evaluation of a vane-type fuel pump that has operated successfully at speeds up to 49,500 rpm and outlet pressures up to 900 psig. The objective of the research was to produce a main-engine fuel pump for small gas-turbine engines capable of operating at engine shaft speed in order to reduce the bulk and complexity of the required gear drive train. The pump has a design JP-4 turbine-fuel flow rate of 2000 lb/hr at 650 psig. The successful completion of a 200-hr endurance run has verified that the high-speed capabilities have been achieved without sacrificing pump endurance life.

scholarly journals Development of High Efficient Industrial Gas Turbine Engines Based on NK-Series Aeroengine Family

1991 ◽  
Author(s):  
N. D. Kuznetsov ◽  
V. N. Orlov ◽  
K. V. Kahovsky
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Gas Turbines ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
High Efficient ◽  
Industrial Gas Turbines ◽  
Industrial Gas Turbine

The paper gives principles of aeroengines conversion into industrial gas turbines. New constructive solutions for designing gas turbines with thermal efficiency 38% are discussed. Data are based on KSPA “TRUD” experience of NK-12 and NK-8 aeroengines conversion.

scholarly journals Design Features of the ГТД 8000 and ГТД 15000 Marine Gas Turbine Engines

1992 ◽  
Author(s):  
Victor I. Romanov
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
High Performance ◽  
Performance Data ◽  
Design And Technology ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Features ◽  
And Performance ◽  
New Generation

This paper describes design features and performance data of the ГТД 8000 and ГТД 15000 engines of new generation. The efficiency of these engines is 34–35% (simple cycle, ISO Conditions). The paper presents basic trends of design and technology improvements resulted in a high performance engine. Examples of new gas turbines application are shown.

scholarly journals A Microprocessor Based Hierarchical Control System for Gas Turbines

1978 ◽  
Author(s):  
D. M. Risch ◽  
D. Goar
Keyword(s):  
Control System ◽  
Gas Turbines ◽  
Hierarchical Control ◽  
Turbine Engines ◽  
System Control ◽  
Total System ◽  
Gas Turbine Engines ◽  
System A ◽  
Analog Control ◽  
Industrial Gas Turbines

Electronic controls are being used on more gas turbine engines today than ever before. Part of this has been due to the proven capability of electronics, and part has been due to the increasingly complex tasks that controls have been required to perform. Unfortunately, for industrial gas turbines, there has been little coordination between the various aspects of the total system: control, sequencing, monitoring, and annunciation. This paper describes a control system which has integrated all those functions into a hierarchical system that is both powerful and reliable. The key elements of the system are a microprocessor controlled programmable sequencer and a proven modular analog control system. A gas pipeline application will be explored in detail.

scholarly journals Progress in Novel Electrodeposited Bond Coats for Thermal Barrier Coating Systems

Materials ◽  
2021 ◽  
Vol 14 (15) ◽  
pp. 4214
Author(s):  
Kranthi Kumar Maniam ◽  
Shiladitya Paul
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Gas Turbines ◽  
High Performance ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Potential Cost ◽  
Bond Coats ◽  
Barrier Coating

The increased demand for high performance gas turbine engines has resulted in a continuous search for new base materials and coatings. With the significant developments in nickel-based superalloys, the quest for developments related to thermal barrier coating (TBC) systems is increasing rapidly and is considered a key area of research. Of key importance are the processing routes that can provide the required coating properties when applied on engine components with complex shapes, such as turbine vanes, blades, etc. Despite significant research and development in the coating systems, the scope of electrodeposition as a potential alternative to the conventional methods of producing bond coats has only been realised to a limited extent. Additionally, their effectiveness in prolonging the alloys’ lifetime is not well understood. This review summarises the work on electrodeposition as a coating development method for application in high temperature alloys for gas turbine engines and discusses the progress in the coatings that combine electrodeposition and other processes to achieve desired bond coats. The overall aim of this review is to emphasise the role of electrodeposition as a potential cost-effective alternative to produce bond coats. Besides, the developments in the electrodeposition of aluminium from ionic liquids for potential applications in gas turbines and the nuclear sector, as well as cost considerations and future challenges, are reviewed with the crucial raw materials’ current and future savings scenarios in mind.

Advances in coupled axial turbine and nonaxisymmetric exhaust volute aerodynamics for turbomachinery

2020 ◽  
pp. 095441002096645
Author(s):  
Jie Gao ◽  
Chunde Tao ◽  
Dongchen Huo ◽  
Guojie Wang
Keyword(s):  
Performance Improvement ◽  
High Efficiency ◽  
Three Dimensional ◽  
Great Influence ◽  
Aerodynamic Characteristics ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Axial Turbine ◽  
Flow Interactions ◽  
And Performance

Marine, industrial, turboprop and turboshaft gas turbine engines use nonaxisymmetric exhaust volutes for flow diffusion and pressure recovery. These processes result in a three-dimensional complex turbulent flow in the exhaust volute. The flows in the axial turbine and nonaxisymmetric exhaust volute are closely coupled and inherently unsteady, and they have a great influence on the turbine and exhaust aerodynamic characteristics. Therefore, it is very necessary to carry out research on coupled axial turbine and nonaxisymmetric exhaust volute aerodynamics, so as to provide reference for the high-efficiency turbine-volute designs. This paper summarizes and analyzes the recent advances in the field of coupled axial turbine and nonaxisymmetric exhaust volute aerodynamics for turbomachinery. This review covers the following topics that are important for turbine and volute coupled designs: (1) flow and loss characteristics of nonaxisymmetric exhaust volutes, (2) flow interactions between axial turbine and nonaxisymmetric exhaust volute, (3) improvement of turbine and volute performance within spatial limitations and (4) research methods of coupled turbine and exhaust volute aerodynamics. The emphasis is placed on the turbine-volute interactions and performance improvement. We also present our own insights regarding the current research trends and the prospects for future developments.

Design, Development and Application of Vehicle Gas Turbine Engines

1966 ◽  
Vol 181 (1) ◽  
pp. 149-172
Author(s):  
P. A. Phillips ◽  
Peter Spear
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Low Cost ◽  
Engine Performance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Development ◽  
Turbine Engine ◽  
Wide Range ◽  
Cycle Temperature

After briefly summarizing worldwide automotive gas turbine activity, the paper analyses the power plant requirements of a wide range of vehicle applications in order to formulate the design criteria for acceptable vehicle gas turbines. Ample data are available on the thermodynamic merits of various gas turbine cycles; however, the low cost of its piston engine competitor tends to eliminate all but the simplest cycles from vehicle gas turbine considerations. In order to improve the part load fuel economy, some complexity is inevitable, but this is limited to the addition of a glass ceramic regenerator in the 150 b.h.p. engine which is described in some detail. The alternative further complications necessary to achieve satisfactory vehicle response at various power/weight ratios are examined. Further improvement in engine performance will come by increasing the maximum cycle temperature. This can be achieved at lower cost by the extension of the use of ceramics. The paper is intended to stimulate the design application of the gas turbine engine.

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure

1990 ◽  
Author(s):  
Yoshiharu Tsujikawa ◽  
Makoto Nagaoka
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Specific Impulse ◽  
Optimization Procedure ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Scramjet Engine ◽  
Aero Engines

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including scramjet engine) to achive the maximum performance. The optimization of such criteria as thermal efficiency, specific output and total performance for gas turbine engines, and overall efficiency, non-dimensional thrust and specific impulse for aero-engines have been performed by the optimization procedure with multiplier method. The comparisons of results with analytical solutions establishes the validity of the optimization procedure.

Pressure Gain Combustion Application to Marine and Industrial Gas Turbines

2012 ◽  
Author(s):  
Philip H. Snyder ◽  
M. Razi Nalim
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Technology Development ◽  
Innovative Technology ◽  
Turbine Engines ◽  
Specific Work ◽  
Compression Pressure ◽  
Pressure Gain Combustion ◽  
Industrial Gas Turbines ◽  
Incremental Improvement

Renewed interest in pressure gain combustion applied as a replacement of conventional combustors within gas turbine engines creates the potential for greatly increased capability engines in the marine power market segment. A limited analysis has been conducted to estimate the degree of improvements possible in engine thermal efficiency and specific work for a type of wave rotor device utilizing these principles. The analysis considers a realistic level of component losses. The features of this innovative technology are compared with those of more common incremental improvement types of technology for the purpose of assessing potentials for initial market entry within the marine gas turbine market. Both recuperation and non-recuperation cycles are analyzed. Specific fuel consumption improvements in excess of 35% over those of a Brayton cycle are indicated. The technology exhibits the greatest percentage potential in improving efficiency for engines utilizing relatively low or moderate mechanical compression pressure ratios. Specific work increases are indicated to be of an equally dramatic magnitude. The advantages of the pressure gain combustion approach are reviewed as well as its technology development status.

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