TWIN TURBO CROSS TUBULAR COMBUSTOR THROUGH TURBO CHARGER (TTX2TT)

Project Title

TWIN TURBO CROSS TUBULAR COMBUSTOR THROUGH TURBO CHARGER (TTX2TT)

Project Area of Specialization Mechatronics EngineeringProject Summary

We have to do experimental analysis on the basis of a new design incorporating 2 turbo chargers , 2 combustion chambers that are connected in a cross such that the first turbo charger works for the first combustion chamber and the second turbo charger uses the the discharge of the first combustion chamber and then works for the second combustion chamber. We have to assure that our project is feasible experimentally , on anysys simulation we already got the desired results. We will then have to calculate the thrust to weight ratio and then we will have to check that in comparision to other turbo jet engines that are being used presently where it stands, according to our calculations this new design expirment will give greater performance , cost will be minimized greatly, fuel consumption will also decrease and power will be enhaced as a whole it will be more effecient  experimentally , in the designing phase on ansys it is sound . We will calculate the pressure and velocity that will be used for the expermental analysis. 

Project Objectives

• Design, simulate and construct a small-scale jet engine.
• This from an already existing turbocharger. The old system used only one turbo charger and the deisgns are axial , we will use 2 turbo chargers and design will be radial & crossed.
• Design and manufacture the combustion chamber .
• Design and manufacture the propelling exhaust nozzle. 

Project Implementation Method

Experimental analysis will be done by Fabrication techniques such as Gas welding, metal forming processes provided with hydrodynamic lubrication and variables will be calculated on running conditions which will be fed into Ansys to obtain Pressure Velocity contours and thrust will be canculated by a Dynamometer.

Benefits of the Project

• The cost of Turbojet engine that are used  is quite high in miillions which can be reduced greatly. 
• The  “Twin  Turbocharged  Cross  Dual  Tubularcombustor”  turbojet  engine,  TTX2Tc,  Have a  calculated  performance  of  Pr  over  4  bar,  TIT  at  1150  K,  SFC  under  0.12  kg/N  hr  and  a momentum  thrust  about  700  N.  These  values  were  better  than  our  object  and  are  considered as  performance  worth  competing  with  other  small  scale  jet  engines.
• The thrust to weight ratio compared to other jet engines is quite  high.
• It will give better performance , pressure losses will also be reduced due to new and improved design. 
• Our engine can also be used in drones, and can replace the old engine that are being used.
• This new design reduces cost quite greatly .
• In pakistan presently there is no industry regarding turbo jet engines so it will be a break through, we will become independant.
•  This can be used for military purposes for the survelliance also. 
• Jet engines that are presently being used cannot go to higher altitudes due to their limitation by their engines , if drones will incorporate our designed engines then they can go to much higher altitudes due to higher thrust to weight ratio.

Technical Details of Final Deliverable

During  the  project  time  the  engine  design  concept  has  changed  from  a  hydrogen  axial concept  till  a  reversed  flow  turbocharged  platform  further  to  the  recent design;  Twin Turbocharged  Cross  Dual  Tubular  combustor  (TTX2Tc),  which  has  taken  a  deviating appearance  in  comparison  to  the  classical  axial  small  scale  turbojet.  The  TTX2Tc  is  based  on two  identical  engine  segments  with  a  turbocharger  unit,  combustion  chamber  and  propelling nozzle.  These  two  sets  together  create  a  crossed  system  for  the  fluid  flow  which  gives  some advantage  of  fewer  parts  to  analyze. For  this  configuration  to  work,  five  subsystems  are  designed  from  products  available  on the  market  which  will  serve  the  engine:  A  Propane  fed  fuel  system  that  is  capable  to  deliver a  sufficient  amount  of  fuel,  an  oil  system  that  provide  the  bearing  with  lubricant  to  sustain the  high  rotational  speed,  a  pressurized  start  system  to  accelerate  the  turbo  shaft,  a  ignition system  to  start  the  combustion  process  and  a  experimental  engine  frame  for  tests  and verifications.  This  analytic  design  is  created  to  be  a  complete  and  functional  jet  engine  after the  manufacturing  and  assembling. The  current  engine  design  also  has  potential  of  performance  improvement  and  further development  such  as  an  alternative  fuel  system  for  bio  or  hydrogen  fuels,  adaptation  for  a bypass  ratio  or  an  extra  turbocharger  stage,  addition  of  an  regulation  and  control  system  and other  subsystem  improvements. 

The  concept  and  the  innovative  part  of  the  TTX2Tc  are  that  two  turbochargers  is  used  and that  those  are  interconnected  through  the  combustion  chambers.  The  engine  apart  from  its subsystems  consists  of  two  turbochargers,  two  combustion  chambers  and  intake-  and  outlet nozzle.

Final Deliverable of the Project Hardware SystemCore Industry ManufacturingOther Industries Transportation Core Technology OthersOther TechnologiesSustainable Development Goals Industry, Innovation and Infrastructure, Responsible Consumption and Production, Partnerships to achieve the GoalRequired Resources

Item Name	Type	No. of Units	Per Unit Cost (in Rs)	Total (in Rs)
			Total in (Rs)	60500
Turbo charger	Equipment	2	10000	20000
DC Motor 12 volt	Equipment	2	1500	3000
Ignition coil	Equipment	2	3000	6000
Oil pump 8W	Equipment	2	1200	2400
Sheet metal (MS & SS)	Equipment	1	10000	10000
Battery 12v	Equipment	1	2500	2500
Pressure gauge	Equipment	2	800	1600
Thermo couple	Equipment	2	1500	3000
Blower	Equipment	2	3000	6000
Transport	Miscellaneous	1	6000	6000