Estimating Mission Performance of an Engine Cycle and Creating Its Gas Flow Path Size

The project of Estimating Mission Performance of an Engine Cycle and Creating Its Gas Flow Path Size aimed to estimate the mission performance of a specific engine cycle and create the gas flow path size of that engine cycle. The project involved thermodynamic modelling, digital simulation, and GFP layout. The project group consisted of team members with different responsibilities. The project applied critical thinking, reasoning, decision making, and systems evaluation skills. The project identified issues related to compression ratio and gas flow path instability and provided solutions. The plan was to produce creative and innovative work by segregating responsibilities and taking proper follow-ups.

CE 1.1 Project Information
Name of the project: Estimating Mission Performance of an Engine Cycle and
Creating Its Gas Flow Path Size
Location of the project: Please fill
Project Duration: Please fill
Organization: Please fill
Role and Designation during the time: Team Member of the project
CE 1.2 Project Background
CE 1.2.1 Characteristics of the project
The project of Estimating Mission Performance of an Engine Cycle and Creating Its
Gas Flow Path Size was my first major project in aeronautical engineering career. The major
purpose of the project was to create a specific set of the various conceptual designing tools
and finally demonstrating the utilizations in several features. It is the proper analysis of a
subsonic civil jet aircraft that helps in simulating the total performance of the propulsion
system and other aircrafts. The proper evaluation of the engine cycle is not done in isolation
and thus the integration between engine airframe missions must be checked. We have
undertaken a particular case study in this project. The case study involved a basic computer
model for performing the mission analysis of the provided engine aircraft system. A digital
simulation is also done for the proper state performances of the aero gas turbine engine.
CE 1.2.2 Objectives developed for the project
The project of Estimating Mission Performance of an Engine Cycle and Creating Its
Gas Flow Path Size consisted of various important objectives. They are as follows:

 To estimate the mission performance of a specific engine cycle.
 To create the gas flow path size of that engine cycle.
CE 1.2.3 My area of work
My major area of work was to make the estimate of the engine cycle for the given
case study. I was responsible for the thermodynamic modelling and the digital simulation for
steady performance of an aero gas turbine engine. My other areas of work were to check on
the aero thermo mechanical compatibility with the help of demonstrating by the GFP or gas
flow path layout. I even checked the GFP size of the engine and the weight of the engine. the
estimation of weights was done properly and thus computer simulation and validation were
also done by me.
CE 1.2.4 Project Group
Figure 1: People involved in the project

CE 1.2.5 My responsibilities throughout the project
I had various important responsibilities in this project. My first and the foremost
responsibility was to estimate the mission performances of the selected engine cycle. I
ensured that the provided mission requirements were the most important and vital for the
project. I was even responsible for calculating or estimating the gas flow path or GFP size as
well as weight. The proper computer simulation and the computer validation were also done
by me. The control of the budgetary aspects or finances was also my significant duty. I made
sure that the project does not exceed the decided budget and hence was responsible for the
overall successful execution of the project. I also researched about the design and
performance of the aircrafts and thus the performance as well as the flight mechanics was
noted by me. The aircraft translational motions were also checked by me. I even involved
various propulsion concepts within the project.
CE 1.3 Distinctive Activity
CE 1.3.1 Engineering knowledge and skills applied in the project
Several aeronautical skills and knowledge were applied in the project by me for
successfully executing it. The first and the foremost aeronautical skill and knowledge that I
had applied is the critical thinking power. Being an aeronautical engineer, critical thinking is
considered as the most important skill that is required for every project. The logic and
reasoning skills were also applied for the successful identification of all strengths and
weaknesses of every alternative solution or approaches to problems. Decision making was
another important skill that I have applied here for taking the decision between various
alternative solutions. Systems evaluation was also done by me for solving the issues.

CE 1.3.3 Comprehending the Theory of Project
This project of estimation of the mission analysis of any specific engine cycle and the
creation of gas flow path or GFP size was accomplished by the help of engine
thermodynamic modelling. The engine operation will have a series of thermodynamic
process. Each process is accomplished by a particular component. All the components are
stacked together to create a propulsion concept. The steady state analysis of the
thermodynamic model is done both on design point steady analysis and off-design point
steady analysis.
The mission analysis was done in the designing point and it helped in finding the
value of the TOGW. According to the requirements of the customer, the gross weight is
guessed and hence the empty weight which is the function of total gross weight. Different
aerodynamic parameters like maximum lift coefficient, wing loading, maximum lift to drag
ratio, aspect ratio and Oswald efficiency. The whole concept of estimating weight of fuel
consumed during mission profile is done in C++ software.
This project has described the basic mathematical basis of the engine GFP weight and
sizing estimation, and also their distinct computer validation, simulation, as well as
application to the best engine cycle that would be considered as the future of civil aircraft.
The CSA in the beginning was performed a drag or a thrust matching for the
successful determination if this installed thrust has the demand of the selected design at the
present mission segment. If the answer is yes, it eventually computes the consumed fuel in
the mission leg as the products of thrust that is engine installed, and the time of mission
segment flight. When the demand of thrust of any other mission segment has exceeded the
highest available thrust that is installed and that the option of aircraft design is infeasible. The
air that has entered within the engine gets split into the major streams at specific fan exit.
When the bypass stream subsequently passes by any annular bypass duct, the major stream

goes by the low pressure or LP compressor, high pressure or HP compressor, HP or LP
turbines and combustor.
The primary as well as the secondary cycle variables in the designing point is
completely user specified. TETDP is being obtained as the TETDP=TETmax/TR, where
TETmax and TR are known as the primary cycle variables. We have chosen a 550 seats
passenger’s aircraft and various literature survey has been done in order to meet the above the
requirements for a civil aircraft which leads to various mission and aerodynamic parameters.
The chosen engine cycle preliminary design could be considered as completed only when
defining of the GFP or gas flow path or the engine envelope layout.
CE 1.3.4 Identified issues and their solutions
1.3.4.1 Issues
There were some of the most significant issues that became major issues for the
successful execution of the project of Estimating Mission Performance of an Engine Cycle
and Creating Its Gas Flow Path Size. The first significant issue that occurred in this project
was during change in the volumes within TDC or top dead centre and BDC or bottom dead
centre. The ratio of these volumes is calculated by V1/V2 and is termed as the compression
ratio. This particular ratio was extremely important for the result of the project. However, the
ratio was coming wrong and due to this our project result was also erroneous. The second
significant issue that we had faced in the project was during modeling of the gas phase. The
mean free path of the gas flow path, when compared to the device length scale, the flow of
gas was absolutely unstable in nature. Due to this, we were not being able to measure the
high pressure and take up several measures to solve the other issues.
1.3.4.2 Solutions

I suggested relevant solutions to all the above mentioned issues or problems and thus
our problems were easily resolved. For the first significant issue of change in the volumes
within TDC or top dead centre and BDC or bottom dead centre, I suggested to take the cut off
ration of V3 and V2. These two volumes were the volumes of the ending and the starting of the
specific combustion phase. The cut off ratio of V3/ V2 was eventually taken into consideration
and hence our problem was solved. This helped us in resolving our issue of wrong volume
ratio and we were able to get proper outcomes for the project. For the second issue of gas
flow path, I provided the suggestion that the development of the multi phase metering
technology for the gas flow. The transient modeling of the flow of gas within the pipelines
were notified in the project by me. Hence our problems were easily resolved in the process.
CE 1.3.5 Plan to produce creative and innovative work
Our plan was to produce creative as well as innovative work by means of segregating
all our works equally. We decided that each of us would execute our given responsibilities
with utmost sincerity and importance. We even decided to take proper follow ups of our
project for avoiding the delays and individual flaws.