Composite Structures lab
Modular 2S Vacuum assisted resin transfer molding system.
Description:
The MODULAR 2S is a single pump / single resin trap mobile vacuum system for manufacturing composites using processes such as resin infusion and vacuum bagging.
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Thin Cylinder Apparatus
Description:
Is to investigate stresses and strains in a thin-walled cylinder under internal pressure. Steel cylinder working to 70 bar. Cylinder fitted with 6 strain gauges wired to a selector switch. Self-contained hydraulic pump and flow control valve and bourdon tube pressure gauge.
Product Code : ELSHADDAI - 0777
Send A EnquirySupersonic Wind Tunnel
Specifications:
Operational stagnation pressure = 8 bar
Volume of storage tank = 3 ft dia X 7 ft length X 2 no
Steady state run time = 30 seconds
Compressor of suitable of 20HP capacity
Suitable air drier
Instrumentation consisting of PC board
Air receiver tank 1500 ltr (vertical) 2.NO
Air receiver tank 2500 ltr (vertical)
Air dryer
Air cooled air cooler
Product Code : ELSHADDAI - 0777
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Supersonic Wind Tunnel
Specifications:
Operational stagnation pressure = 8 bar
Volume of storage tank = 3 ft dia X 7 ft length X 2 no
Steady state run time = 30 seconds
Compressor of suitable of 20HP capacity
Suitable air drier
Instrumentation consisting of PC board
Air receiver tank 1500 ltr (vertical) 2.NO
Air receiver tank 2500 ltr (vertical)
Air dryer
Air cooled air cooler
Product Code : ELSHADDAI - 0777
Send A EnquiryWind Tunnel
This is an open circuit Wind Tunnel which provides a region of controlled airflow into which models can be inserted. The propulsion is provided by a fan at downstream of working section. The tunnel consists of bell mouth shaped entry to guide the air smoothly into settling chamber consisting of honeycomb and nylon mesh screens which filters and stabilizes the air flow. This follows working section or test section where various models can be tested.
Product Code : ELSHADDAI AE - 001
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Sub Sonic Wind Tunnel
This is an open circuit Wind Tunnel which provides a region of controlled airflow into which models can be inserted. The propulsion is provided by a fan at downstream of working section. The tunnel consists of bell mouth shaped entry to guide the air smoothly into settling chamber consisting of honeycomb and nylon mesh screens which filters and stabilizes the air flow. This follows working section or test section where various models can be tested.
Product Code : ELSHADDAI AE - 001
Send A EnquiryCentrifugal Blower Test Rig
The Centrifugal Compressor Test Rig consists of a centrifugal blower driven by a variable speed electric motor. A motor controller is used to regulate the blower speed. Ducts are fitted to inlet & outlet of the blower. A damper in inlet duct is provided to regulate the intake air flow of the blower. A Pitot tube with differential manometer is used to measure the air flow rate. Two manometers are provided to measure intake & discharge pressure of air.
Product Code : ELSHADDAI AE - 002
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Beam Test Setup
A bench mounted beam apparatus to allow students to investigate the deflections and reactions in simply supported and cantilevered beams
Product Code : ELSHADDAI AE - 003
Send A EnquiryForced Convection Apparatus
Average surface heat transfer coefficient for a pipe losing heat by forced convection to air flowing through it can be obtained for different air flow and heat flow rates. The unit consists of a circular pipe, loosing heat by forced convection to air, being forced through it. Constant heat flux is added to pipe by an electrical heater, provided with input control. The pipe surface temperature is measured at various points along length of pipe using thermocouples. Temperature of air at inlet and outlet of test section is measured using temperature indicator.
Product Code : ELSHADDAI AE - 004
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Propeller Test Rig
In this test rig, performance of a Propeller can be investigated. The propeller is mounted on a shaft of DC motor. The load cell arrangement is used to measure the thrust force produced by the propeller.
Product Code : ELSHADDAI AE - 005
Send A Enquiryhele shaw apparatus
Working Section : Made of two laminated glass / acrylic sheets which are closely spaced and fixed in a leak proof moulding
Flow table : Width = minimum 300mm,Length = minimum 500mm,
Dye Tank With Flow Control : Stainless steel tank with minimum 1L capacity Dye injection facility
Sump Tank : Stainless steel tank with minimum 40L capacity
Water circulation : Suitable capacity pumpProduct Code : ELSHADDAI DYN - 002
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Flow Visualization Apparatus
The unit uses water as the flow medium. A contrast medium (dye) is injected through small needles into the flow area. Various drag bodies (included) can be placed in the area of flow. In addition, sources and sinks can be simulated and illustrated using eight additional openings in the flow area.
Product Code : ELSHADDAI AE - 006
Send A Enquiry1. MEASUREMENT OF BURNING VELOCITY OF PRE-MIXED FLAME(PROPULSION- LAB)
Measurement of burning velocity of a Pre-mixed flame. Specially designed burner with wire mesh(2) to generate a laminar pre-mixed flame, Gaseous fuel from the fuel supply through an orifice in to the mixing chamber, velocity of jet is varied Gas Rota meter with control valve for gas flow.
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2. MEASUREMENT OF NOZZLE FLOW (PROPULSION- LAB)
To measure the pressure distribution in nozzle. Study of a
series of convergent and convergent-divergent nozzles. Consists of:
Convergent nozzle of inlet dia 90 mm outlet dia 25 mm length 200 mm
(appx), Multi-bank manometer (acrylic)with 11 groves
U-Tube manometer with Pitot tube for velocity measurement
U-Tube manometer with Orifice plate for Discharge measurement
Centrifugal blower with flow control valve/plate.
Product Code : ELSHADDAI AE - 006
Send A Enquiry3. CASCADE WIND TUNNEL (PROPULSION- LAB)
Cascade testing of a model of axial compressor blade row and turbine cascade. The blades of an axial compressor and axial turbine have high solidity which makes the flow structure in these machines highly complex as the flow around each blade is affected by the presence of the adjacent blades.
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4. PROPELLER TEST RIG (PROPULSION- LAB)
Propeller Test Rig is a special test rig. In this test rig, performance of a Propeller can be investigated. The propeller is mounted on a shaft of DC motor.
Send A Enquiry5. FORCED CONVECTIVE HEAT TRANSFER OVER A FLAT PLATE (PROPULSION- LAB)
Study of convective heat transfer over a flat plate in
forced air condition. Consists of:
Uniformly heated flat plate (Aluminum)& maintained at constant
temperature by
using heat control with Electronic regulator. Heater size : 150X150 mm &
capacity 250 Watts (approx.) Centrifugal blower / fan with duct & flow
control by speed control of blower. Digital Anemometer for air Velocity
measurement Outlet line Duct of size1000mmX250mm Digital temperature
indicator & channel selector with thermocouples on heated surface
6. AXIAL FLOW COMPRESSOR TEST RIG (3 STAGES). (BASIC MODEL) (PROPULSION- LAB)
In an axial-flow compressor, air passes from one stage to the next with each ... and the second set of combustors are located between the high-pressure and the ... a blade element showing wm, the appropriate velocity upon which to base the lift ... model will not be accurate and careful consideration of the three-dimensional
Send A Enquiry7. WATER FLOW CHANNELS & MODELS(PROPULSION- LAB)
The model is both general and flexible in that it can be used to simulate a wide range of flow conditions for various channel configurations. ... Discharges and water-surface elevations computed at intermediate locations within a channel are determined following solution of the transformation equations.
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8. BOYS GAS CALORIMETER (For LPG and liquid fuel) (PROPULSION- LAB)
Introduction Boy's gas calorimeter was designed to get accurate values of the higher and lower calorific value of given fuel. Mainly we can measure the calorific value of gaseous fuels only because the practical apparatus was designed for that purpose.
Send A Enquiry9. STUDY OF FREE JET & WALL JET SETUP(PROPULSION- LAB)
The orifice and free jet flow apparatus consists of a
cylindrical head tank with an .. Install the 3-mm orifice in the fitting
on the right-hand side of the head tank Centrifugal blower with a flow
control valve,
U-Tube Manometer with a pitot tube for jet velocity measurement.
U-Tube Manometer with a orifice plate for discharge measurement.
Venturi Duct with a Honeycomb / mesh for smooth flow.
For jet force measurement on testing plate with digital indicator and
load cell
10. RADIAL 14 CYLINDER PISTON ENGINE (PROPULSION- LAB) (PROPULSION- LAB)
We are leading of doing cut works in Aircraft Piston Engine Cut-section for easily understanding the working principles
The radial engine is a reciprocating type internal combustion engine configuration in which the cylinders point outward from a central crankshaft like the spokes of a wheel. It resembles a stylized star when viewed from the front, and is called a "star engine" (German Sternmotor) in some languages. The radial configuration was very commonly used in aircraft engines before turbine engines became predominant.
Send A Enquiry10. RADIAL 14 CYLINDER PISTON ENGINE (PROPULSION- LAB) (PROPULSION- LAB)
We are leading of doing cut works in Aircraft Piston Engine Cut-section for easily understanding the working principles
The radial engine is a reciprocating type internal combustion engine configuration in which the cylinders point outward from a central crankshaft like the spokes of a wheel. It resembles a stylized star when viewed from the front, and is called a "star engine" (German Sternmotor) in some languages. The radial configuration was very commonly used in aircraft engines before turbine engines became predominant.
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11. JET ENGINE(PROPULSION- LAB)
An engine that produces motion as a result of the rearward discharge of a jet of fluid specifically: an airplane engine that uses atmospheric oxygen to burn fuel and produces a rearward discharge of heated air and exhaust gases.
Send A Enquiry12. DUCT BURNER TESTRIG(PROPULSION- LAB)
Duct burners are designed to work inside heat-recovery steam
generator (HRSG) in order to increase the heat energy of a gas turbine
exhaust. Duct burners guarantee maximum flame stability and reliability
providing low emissions on a wide variety of applications.
Duct Burners to resist to the high temperature inside the duct and to
provide long equipment life for components since they are used in
combined cycles and they can work either with fresh air (when gas
turbine is turned off) or exhaust gas. These burners are usually
provided in multiple row and they are designed in modular configuration
for an easy construction and maintenance.
13. AXIAL COMPRESSOR (FLOW FAN) TEST RIG (PROPULSION- LAB)
Axial flow compressors are very important part of jet engines gas turbines. The 'DYNAMIC' unit is a single stage axial flow compressor with guide vanes on upstream and downstream. The angle of guide vanes is also variable. compressor blades are of standard aerofoil shape. The compressor is also driven by a variable speed motor hence, characteristics of compressor can be drawn with various variables. axial flow compressors are generally characterized by large hub - tip ratio, higher pressure rise, higher temperature rise and smaller pitch - chord ratio. Hence presence of both axial flow fan and axial flow compressor presents the students a good comparison between the two.
Send A Enquiry14. BLOWER BALANCE AND SMALL ASPECT RATIO (PROPULSION- LAB)
The Blower is coupled to an induction motor of 3HP. The Blower is coupled with a Dynamometer type motor with a stepped pulley arrangement to run at three different speeds, balance arm, dial type spring balance with a large size dial etc., to determine the input power of the blower. Instrumentation.
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15. FLAME PROPAGATION UNIT (PROPULSION- LAB)
An instrumentation console provides an adjustable and measured flow of both air and gas. Two flowmeter in series, ensure that a wide range of typical slow burning gaseous fuels (e.g. Propane, Butane, Methane LPG) can be used and measured accurately.
Send A Enquiry16. RAMJET ENGINE (PROPULSION- LAB)
A jet engine that consists essentially of a hollow tube without mechanical components and depends on the aircraft's speed of flight to compress the air which is supplied to a burner from which hot gases are discharged rearward Ramjet Engine Diffuse Diameter:0.036m Overall Length :0.650 M Thickness:0.0016m Nozzle Angle :16 Degree Material:Heat Resistant Alloy Steel (Stainless Steel) Fuel Used:Gasoline Fuel Delco Motor Unit Connected With Magneto Ignition Fuel
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17. CASCADE WIND TUNNEL WITH COMPRESSOR AND TURBINE BLADE (PROPULSION- LAB)
The objective of this research work is to study the behaviour of flow at the inlet, within the blade passage and at the exit of a compressor cascade. For this purpose, a cascade with six numbers of aerofoil blades was designed and constructed. The cascade was fitted on the cascade test tunnel. Out of six blades two were instrumented for measuring the pressure distribution on the pressure and suction surface. The blades had a parabolic camber line, with a maximum camber position at 40% of the chord from the leading edge of the blade.
Send A Enquiry17. CASCADE WIND TUNNEL WITH COMPRESSOR AND TURBINE BLADE (PROPULSION- LAB)
The objective of this research work is to study the behaviour of flow at the inlet, within the blade passage and at the exit of a compressor cascade. For this purpose, a cascade with six numbers of aerofoil blades was designed and constructed. The cascade was fitted on the cascade test tunnel. Out of six blades two were instrumented for measuring the pressure distribution on the pressure and suction surface. The blades had a parabolic camber line, with a maximum camber position at 40% of the chord from the leading edge of the blade.
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