| S.NO | NAME OF THE EQUIPMENT | QUANTITY | SPECIFICATIONS |
|---|---|---|---|
| 1 | Brinel and hardness testing machine | 1 | ---- |
| 2 | Universal Testing Machine | 1 | Capacity: 400 KN. Model: UTK-40. SR.No: 2013/1073. Mfd. By: Krystal Equipments, Ichalkaranji, M.H, India. |
| 3 | Torsion Testing Machine | 1 | Capacity: Torque Range: 0-10 Kg-m. Model: TTM-10.. SR.No: 2001/1012. Mfd. By: Macro Testing Machines, Ichalkaranji, M.H, India. |
| 4 | SpringTesting Machine | 1 | Capacity: 0-250 Kgf. Model: MX-250 SR.No: 2001/1001. Mfd. By: Macro Testing Machines, Ichalkaranji, M.H, India. |
| 5 | Izod Impact Testing Machine | 1 | Capacity: Energy range: i. Charpy: 0-300 J.
ii. Izod: 0-168 J. Model: ITM-300 SR.No: 2001/1016. Mfd. By: Macro Testing Machines, Ichalkaranji, M.H, India. |
| 6 | Bending test on Simple supported beam | 1 | Nil |
| 7 | Bending test on Cantilever beam | 1 | Nil |
| 8 | Charpy Impact test | 1 | Capacity: Energy range: i. Charpy: 0-300 J.
ii. Izod: 0-168 J. Model: ITM-300 SR.No: 2001/1016. Mfd. By: Macro Testing Machines, Ichalkaranji, M.H, India. |
| 9 | Punch shear test | 1 | Nil |
| 10 | Compression Test | 1 | Capacity: 400 KN.
Model: UTK-40. SR.No: 2013/1073. Mfd. By: Krystal Equipments, Ichalkaranji, M.H, India. |
A large number of experiments could be performed in the laboratory to demonstrate the principles of hydraulics and fluid mechanics deals with the different experiments. The main objective of this FLUID MECHANICS AND HYDRAULIC MACHINES LAB is to build fundamental concepts combined with strong analytical and problem solving abilities that would form the backbone of many other subjects in higher educations.
| S.NO | NAME OF THE EQUIPMENT | QUANTITY | SPECIFICATIONS |
|---|---|---|---|
| 1 | IMPACT OF JET ON VANES TEST RIG | 1 | |
| 2 | PELTON WHEEL TURBINE TEST RIG | 1 | PELTON TURBINE 1. Power output: 1 K Watt 2. No. of Buckets: 17Nos. SUPPLY PUMPSET 1. Capacity : 5 HP 2. Type : Centrifugal FLOW MEASURING UNIT 1. Size of Venturi meter : 50 mm. 2. Diameter of inlet : 50 mm 3. Diameter of throat : 25 mm. |
| 3 | FRANCIS TURBINE TEST RIG | 1 | 1. Rated Supply head : 1.2 Meters 2. Discharge : 2000 LPM 3. Rated Speed : 1200 rpm 4. Power Output : 4 HP 5. Runner Diameter : 180 mm 7. No. of guide vanes : 8 8. Brake Drum Diameter : 300 mm |
| 4 | KAPLAN TURBINE TEST RIG | 1 | KAPLAN TURBINE 1. Power output: 1 K Watt 2. No. of Buckets: 17Nos. SUPPLY PUMPSET 1. Capacity : 5 HP 2. Type : Centrifugal FLOW MEASURING UNIT 1. Size of Venturi meter : 50 mm. 2. Diameter of inlet : 50 mm 3. Diameter of throat : 25 mm. |
| 5 | SINGLE STAGE CENTRIFUGAL PUMP TEST RIG | 1 | NIL |
| 6 | MULTI STAGE CENTRIFUGAL PUMP TEST RIG | 1 | NIL |
| 7 | RECIPROCATING PUMP TEST RIG | 1 | NIL |
| 8 | Determination of friction factor for a given pipe line | 1 | 1. Sump tank size : 0.95 m x 0.45 m x 0.3 m S.S. tank 2. Measuring Tank Size : 0.3 m x 0.3m x 0.5 m S.S. Tank 3. Differential Manometer : 1 m range with 1mm scale of graduation 4. No. of pipes : 1S.S, 2 Galvanized Iron(GI) pipes 5. Piping system sizes : 20 mm, 20mm, 12.7mm 6. Pressure taping distance : 0.1 m 7. Pump set : Pump is 25x25mm2 size, centrifugal, moonset pump with single phase, 2pole, 220V, 1/2HP, 50 Hz, 2880 rpm, AC supply. |
| 9 | VENTURIMETER AND ORIFICEMETER TEST RIG | 1 | Sump tank size : 0.3 m x 0.45 m x 0.94 m S.S. Tank 2. Measuring tank size : 0.3 m x 0.3 m x 0.5 m S.S. Tank 3. Differential Manometer : 1.0 m range with 1mm scale graduations 4. Pipe size : 25 mm 5. Venturi meter inlet diameter (d) : 25 mm 1 6. Venturi throat diameter (d ) : 14 mm 2 7. Area ratio (a /a) m : 0.35 2 1 8. Supply pump set : Pump is 25 x 25 mm2 size, Centrifugal Monoset pump with single phase, 2 Pole, 220V, 50Hz, ½ HP, 2780 RPM, AC Supply |
| 10 | FLOW THROUGH PIPES TO STUDY MINOR LOSSES AND MAJOR LOSSES | 1 | 1. Sump tank size : 0.9 m x 0.45 m x 0.3 m S.S. tank 2. Measuring Tank Size : 0.6 m x 0.3m x 0.3 m S.S. Tank 3. Differential Manometer : 1 m range with 1mm scale of graduation 4. No. of pipes : 2 Galvanized Iron(GI) 5. Piping system sizes : 25 mm,12.5mm 6. Pressure taping distance : 0.5 m 7. Pump set : Pump is 25x25mm2 size, centrifugal, moonset pump with single phase, 2pole, 220V, 1/2HP, 50Hz, 2880 rpm, AC supply. |
| 11 | BERNOULLIS APPARATUS | 1 | 1. Sump tank size : 1.25 m x 0.3m x 0.3m S.S. tank 2. Measuring Tank size : 0.3 m x 0.5 m 3. Pump size : 25mm x 25 mm 4. Supply pump set : Pump is centrifugal manometer pump with single phase, 2 pole, 220V, 50 Hz, ½ Hp, 2880 RPM, AC supply |
| S.NO | NAME OF THE EQUIPMENT | QUANTITY | SPECIFICATIONS |
|---|---|---|---|
| 1 | COMPUTER with MATLAB | 16 | MATLAB SOFTWARE |
| S.NO | NAME OF THE EQUIPMENT | QUANTITY | SPECIFICATIONS |
|---|---|---|---|
| 1 | COMPUTERS WITH AUTOCAD SOFTWARE | 16 | AUTOCAD VERSION 2015 |
To make the student understand about the Design and manufacture of simple patterns, Types of welding- Arc welding, Gas welding and spot welding equipment for the Fabrication of welded Joints. The students will understand the manufacturing and Fabrication Processes of the industries which they perform at the laboratory on minor levels.
| S.NO | NAME OF THE EQUIPMENT | QUANTITY |
|---|---|---|
| 1 | Milling machine set up | 1 |
| 2 | External Threading | 1 |
| 3 | Arc welding set up | 1 |
| 4 | Internal Threading | 1 |
| 5 | Lathe Machine set up | 1 |
| 6 | Drilling Machine set up | 1 |
| 7 | Shaper machine | 1 |
| 8 | Cylindrical Grinding Machine | 1 |
| 9 | Slotting machine | 1 |
| 10 | Drilling Machine with tools drills, reaming tools, boring tools | 1 |
| 11 | SPOT WELDING | 1 |
| 12 | TIG WELDING | 1 |
| 13 | PLASMA ARC CUTTING | 1 |
"The Aerodynamics and Propulsion Lab of the Aeronautical Engineering Dept., is well known for Research in the area of Aerodynamics and Propulsion. The lab has all research level facilities. The lab is equipped with Low Speed wind Tunnel with variable speed, where jet mixing studies and flow visualization can be carried out. The lab also houses Heat Engines where Power, Torque, Pressure, Temperature measurement and cycle analysis can be performed also heat balance studies, exhaust gas composition, effect of fuel and flame stability test can be performed
| S.NO | NAME OF THE EQUIPMENT | QUANTITY | SPECIFICATIONS |
|---|---|---|---|
| 1 | Subsonic Wind Tunnel Set up |
1 | Variable speed tunnel |
| 2 | Axial Flow compressor setup | 1 | Number of stages : three stages |
| 3 | Centrifugal flow compressor setup | 1 | Blower : Centrifugal ,with Volute Casing, and |
| 4 | Piston Engine test rig |
1 | - |
| 5 | Balancing Test rig |
1 | - |
| 6 | Bomb Colorimeter |
1 | - |
| 7 | Flash Fire Point apparatus |
1 | - |
| 8 | Viscosity measurement apparatus |
1 | - |
| 9 | Piston Engine for visual inspection & trouble shooting |
1 | - |
The structures laboratory is used to enhance the learning experience of undergraduate students by encouraging them to undertake projects. In addition the structures lab provides facilities which can be used for specimen preparation and testing. The structures lab is set up for experimentation and testing of structural components. The lab is currently being used for a number of research activities involving composite materials, aluminum, wood and other structural materials.
| S.NO | NAME OF THE EQUIPMENT | QUANTITY |
|---|---|---|
| 1 | Universal Testing Machine | 1 |
| 2 | Test rig for shear centre measurement | 1 |
| 3 | Cantilever and simply supported beams along with dial gauges | 1 |
| 4 | NDT equipment : Magnetic particle testing equipment | 1 |
| 5 | NDT equipment : Ultrasonic Testing equipment | 1 |
| 6 | NDT equipment : dye penetration equipment | 1 |
| 7 | Experimental set up to measure the seismic vibrations | 1 |
Flight laboratory is actively involved in the research towards parameter estimation from flight data. Accordingly, the aircraft instrumentation is being upgraded. The laboratory utilizes Microsoft Excel for evaluation of Take-off weight (Gross). Trade-off studies are also performed in labs curricula, Students are required to plot the Aerofoil with various NACA series (Interpolation). Apart from this there is evaluation of Aircraft performance wherein we calculate the Thrust and Power required curves.
| S.NO | NAME OF THE EQUIPMENT | QUANTITY | SPECIFICATIONS |
|---|---|---|---|
| 1 | MAT LAB software | 1 | |
| 2 | Hydraulic system setup | 1 | - |
| 3 | Pneumatic system setup | 1 | - |
| 4 | Landing gear set up equipment | 1 | Simple Retractable Landing gear |
| 5 | Cut models of aircraft equipment | 1 | Fuselage Nose Cone |
The lab is provided with systems installed with ANSYS software, on performing experiments on the ANSYS-Structural Software suite enables the student to solve complex structural engineering problems and make better, faster design decisions. With finite element analysis (FEA) tools, a Student can customize and automate various simulations, and parameterize them to analyze multiple design scenarios. ANSYS structural mechanics software easily connects to other physics analysis tools, providing even greater realism in predicting the behavior and performance of complex products.
| S.NO | NAME OF THE EQUIPMENT | QUANTITY | SPECIFICATIONS |
|---|---|---|---|
| 1 | ANSYS SOFTWARE | 16 | Version-15 |
| 2 | CATIA SOFTWARE | 16 | Version-V5 |
The Lab is provided with Systems installed with ANSYS Software wherein we utilize the Computational Fluid Dynamics (CFD) module for performing of the various analysis(experiments), it is a tool with amazing flexibility, accuracy and breadth of application. It provides students working on it a better insight to help them optimize their designs carefully. ANSYS CFD goes beyond qualitative results to deliver accurate quantitative predictions of fluid interactions and trade-offs. These insights reveal unexpected opportunities for their analysis.
| S.NO | NAME OF THE EQUIPMENT | QUANTITY | |
|---|---|---|---|
| 1 | ANSYS SOFTWARE | 16 | Version-15 |
