Thermal Power Systems

School of Engineering and Design

©2012 Brunel University

Thermal Power Systems
Module Code and Title: Title of Assignment: Academics responsible: ME2301, Thermofluids Thermal Power Lab Report T1 (Gas Turbine), Prof. T. Megaritis T2 (Refrigeration, Dr L. Ganippa Contribution to total module mark: 15% Suggested Allocation time: 20 hours Submission Date: Tuesday 8 January 2013 NO LATER THAN 4:00pm on the submission date to the General Office for FULL credit. Otherwise, a penalty for late submission as specified by the Board of Studies will apply. (NOTE: ANY MITIGATING CIRCUMSTANCES must be notified a.s.a.p. Failure to print work on the project in good time, or other machine-related failure will not be deemed to be a Mitigating Circumstance). Aims: • To show an understanding of the principles of vapour compression refrigeration cycle • To appreciate and apply thermodynamic analysis to a refrigerator • To show an understanding of the principles of a gas turbine power plant Specification of Assignment: The assignment comprises two parts: Part 1: Laboratory report on Refrigeration Experiment Part 2: Brief description of the gas turbine apparatus, its operation and sample calculation Specification of the material to be submitted: Marking Scheme Front cover: Title, name, group number, and the date of experiments Introduction and objectives of the Refrigeration Experiment 5% Sketch and brief description of the Refrigeration Experimental Setup 5% Refrigeration Laboratory Results (sample calculation for one of the tests) 35% Refrigeration Laboratory Discussion and Conclusions 35% Brief description of the gas turbine apparatus, its operation and sample calculation 20%

Attendance to both labs (gas turbine and refrigeration) is compulsory. Marks will be given only to reports of students who attended both labs.

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Thermal Power Systems

School of Engineering and Design

©2012 Brunel University

Assignment/Coursework Performa
Module Code: ME2301 Assessment Title: Thermal Power Lab Report Module Leader

MAIN OBJECTIVES OF THE ASSESSMENT: • To show an understanding of the principles of vapour compression refrigeration cycle • To appreciate and apply thermodynamic analysis to refrigeration systems • To show an understanding of gas turbine power plants

BRIEF DESCRIPTION OF ASSESSMENT: The assignment comprises two parts: Part 1: Laboratory report on Refrigeration Experiment Part 2: Brief description of a gas turbine power plant and sample calculation

LEARNING OUTCOMES FOR THE ASSESSMENT (Refer to the appropriate module learning outcomes) The student will be able to; 1. to carry out an experimental study on a vapour compression refrigeration system 2. to analyse the performance of the refrigeration system. 3. to get ‘hands on’ experience of a lab scale gas turbine system, record operating parameters data and use the data to carry out calculations

ASSESSMENT CRITERIA The student will _ Identify the changes in state and phase of the refrigerant which occur in each component of the refrigeration system. _ Determine the energy transfers which occur for each of the component of the refrigeration system. _ Calculate the refrigerator coefficient of performance (COP) based upon the measured data. _ Understand and describe the operation of a gas turbine plant and perform calculations based upon the measured data.

ASSESSMENT METHOD BY WHICH A STUDENT DEMONSTRATE THE LEARNING OUTCOMES:

CAN WEIGHTING 5% 5% 35% 35% 20% 2

Introduction and Objectives of the Refrigeration Experiment Sketch and Brief Description of the Refrigeration Experimental Setup Refrigeration Laboratory Results (sample calculation for one of the tests) Refrigeration Laboratory Discussion and Conclusions Gas Turbine: Brief description of the gas turbine apparatus, its operation and sample calculation

Thermal Power Systems

School of Engineering and Design

©2012 Brunel University

FORMAT OF THE ASSESSMENT/COURSEWORK: (Guidelines on the expected format and length of submission) Specification of the material to be submitted: Front cover: The assignment sheet, Title, name, group number, and the date of experiments Part A: Vapour Compression Refrigeration Page 1: Introduction and Objectives of the Experiment Page 2: Sketch and Brief Description of the Experimental Setup Page 3: Laboratory Results (sample calculation for one of the tests) Page 4: Discussion and Conclusion Part B Gas Turbine Power Plant Page 1 Brief description of the gas turbine apparatus, its operation and sample calculation Appendix: graphs and tables

ASSESSMENT DATE(S)/SUBMISSION DEADLINE(S) Submission Date: as announced PENALTIES FOR LATE SUBMISSION: NO LATER THAN 4:00pm on the submission date to the General Office for FULL credit. Otherwise, a penalty for late submission as specified by the Board of Studies will apply.

INDICATIVE READING LIST: 1. Manual for Hilton Refrigeration Rig. 2. Module Recommended Thermodynamics Book(s).

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Thermal Power Systems

School of Engineering and Design

©2012 Brunel University

Level 2 Thermofluids Laboratories Thermal Power Experiment 1: Gas Turbine
Industrial gas turbines are usually intended to drive generators or pumps for providing emergency supplies of electricity or water. A schematic of a gas turbine plant is shown in Figure 1. This is a single shaft, open-type gas turbine unit, without any heat exchanger, intercooler, or reheater.

Objectives The purpose of this laboratory exercise is (i) to provide an understanding of the principles of a gas turbine plant; (ii) to get ‘hands on’ experience of a lab scale gas turbine system, record operating parameters at different operating conditions and use the data to carry out calculations. Laboratory Study the gas turbine apparatus and the measuring instruments available and draw a simple diagram that will allow you to prepare a brief description of the apparatus and its operation for your report.

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Thermal Power Systems

School of Engineering and Design

©2012 Brunel University

SR-30 Gas Turbine A pure turbojet, the SR-30 is representative of all straight jet engines in which combustion results in an expanding gas that is sufficiently capable of producing useful work and propulsive thrust. Consisting of a centrifugal flow compressor, annular combustor and axial flow power turbine, the SR-30 engine is typical of the gas generator core found in turbofan, turboprop and turboshaft gas turbine engines, which are typically used for aircraft and marine propulsion, as well as stationary and industrial power generation.

FIG. 1 Engine Sensor Locations RPM Tachometer Generator: (Displayed on Panel as RPM and Data Acquisition Screen). P1: Compressor Inlet Pressure (Displayed on Data Acquisition Screen) T1: Compressor Inlet Temperature (Displayed on Data Acquisition Screen) P2: Compressor Exit Temperature (Displayed on Data Acquisition Screen) T2: Compressor Exit Temperature (Displayed on Data Acquisition Screen) P3: Turbine Inlet Pressure (Displayed on Panel and Data Acquisition Screen) T3: Turbine Inlet Temperature (Displayed on Panel as TIT and Data Acquisition Screen) P4: Turbine Exit Pressure (Displayed on Data Acquisition Screen) T4: Turbine Exit Temperature (Displayed on Data Acquisition Screen) P5: Exhaust Gas Pressure (Displayed on Data Acquisition Screen) T5: Exhaust Gas Temperature (Displayed on Panel as EGT and Data Acquisition Screen) Fuel Pressure: (Displayed on Panel) 5

Thermal Power Systems

School of Engineering and Design

©2012 Brunel University

FIG. 2 Schematic of Brayton Cycle for Gas Turbine and Cut Away of SR-30 Engine1

FIG.3 Ideal Brayton cycle and actual Brayton cycle

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Thermal Power Systems

School of Engineering and Design

©2012 Brunel University

The density of dry air where p is absolute pressure (pABS = pATM + pGAGE), R is the specific gas constant for dry air (287.05 J/(kg.K) in SI units), and T is absolute temperature. Air velocity into compressor and exiting the nozzle Volumetric flow rate of air into compressor and exiting the nozzle Mass flow rate into compressor and exiting the nozzle Thrust at the compressor and nozzle

RECORDING AND USING YOUR DATA PROPERLY IS AN IMPORTANT PART OF SUCCESSFULLY COMPLETING THE LAB.

Your lab demonstrator will run the engine at three different speeds, use the data acquisition software on the computer and log the engine data (speed, thrust, fuel flow, temperature and pressure at different points) for each speed. I. Calculate the air velocity and mass flow rate into compressor and exiting the nozzle at the maximum engine speed. II. Calculate the thrust generated at the compressor and nozzle for the maximum engine speed. NB. The cross sectional area at compressor inlet and nozzle exit are A=0.0031m2 and A=0.0025m2 respectively.

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