Heading operation Calculation of engine of gas pumping unit power plant with capacity of 2.5 MW

Contents

CONTENTS

List of used symbols and main symbols

abbreviations, indexes

Introduction

1. Source Data for Calculation

2. Preliminary calculation

3. Calculation by initial parameters

3.1. Calculation of working medium parameters in characteristic sections of engine flow section

3.2. Calculation of engine basic data

3.3. Preliminary evaluation of geometric parameters of assemblies

in characteristic sections of the engine

3.4. Calculation of rotation speed of gas generator rotors and free

turbines

4. Engine description

Conclusion

List of sources used

Paper

Course work 28 p., 4 Fig., 4 Table, 3 sources.

GAS TURBINE ENGINES, GAS-DYNAMIC DESIGN OF ENGINE, THERMOGASODYNAMIC CALCULATION, CALCULATION OF GEOMETRIC AND KINEMATIC PARAMETERS.

The design object is a turbine engine for a power plant of a gas pumping unit with a capacity of 2.5 MW.

The purpose of the work is to determine optimal parameters of the working process, thermogasodynamic, geometric and kinematic calculation of the turbine engine, calculation of the rotor speed.

Calculations were made on analytical one-dimensional mathematical models on a personal computer using MathCad.

In process of thermogasodynamic calculation parameters of working process, parameters of working medium in characteristic sections, basic data of engine are obtained, preliminary geometric and kinematic parameters of units are determined. Diagram of engine flow section with distribution of working medium parameters along the path is drawn.

As a result, the calculated engine is more economical than the prototype. The effective efficiency of the engine is 0.225 at a specific fuel consumption of 0.32 kg/kWh.

The engine may be recommended for use in terrestrial gas turbine installations.

Introduction

As is known, converted aircraft-type gas turbine engines can be used as low and medium power gas turbine plants.

Historically, until some time, the development of technology and the improvement of the design of stationary and aircraft engines went in parallel courses. However, due to the widespread use of GTDs in military and civil aviation and the significant costs of their development and improvement of technology, aircraft-type engines received a number of advantages over similar stationary ones: higher effective efficiency (up to 40% or more), high quality of production, modularity of design, due to which they were widely used in ground conditions at gas pumping stations and in the electric power industry. Their disadvantage is higher maintenance and repair costs.

Reliability of engines is ensured by long-term finishing and resource tests of a large number of experimental gas turbine engines on ground stands and in flying laboratories, strict regulation of the technology of manufacture, assembly and operation. The necessary economy is achieved by high engine parameters, perfect aerodynamics of turbomachines, rational use of air for cooling of high-temperature parts. Good mass values are ensured due to the principle of mass minimization based on the design by rational use of the material, due to the new technology for producing blanks, the wide use of light alloys and materials with high specific strength (titanium, magnesium and other alloys).

When converting the aircraft engine for operation at combustion chamber, it is necessary to perform a large amount of work due to the type of engines. Reprocessing of a HPT or dual-flow turbojet engine (DTRE) usually includes: replacing the fuel system, replacing the engine suspension (attachment), reducing the maximum speed, gas temperature and compression ratio, removing (silencing) the fan circuit (in the DTRE) or reduction gear in the HPT, changing the hinged units from the engine housing to the frame, replacing the control and automatic control systems. In domestic practice, when converting aircraft engines, power turbines of the transport type on rolling bearings, having a single structural appearance with a gas generator, became widespread. Currently, the GPA fleet with gas turbine drive accounts for more than 80% of the total number of units operated at compressor stations of gas main pipelines. The principles and methods of designing a free power turbine allocated to a separate shaft largely determine the cost-effectiveness of the entire plant.

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