kzbin.info/www/bejne/j4OceGqtnLN_jac

kzbin.info/www/bejne/Y3e2Ymh6bqeWrLM

Pressure will increase as velocity will decrease in a converging section provided the flow is supersonic.

According to continuity equation, as flow area increases (diverges), speed reduces in subsonic flow. Hence you are correct partially.

Thank you. It simplifies the entire design process. Please inform if there is any other reason.

Thank you very much.

Our Chief Mentor studied Design of Gas Turbines at the IIT Madras. However all the design was taught on the black-board. No gas Turbine engine was ever shown. So our Chief Mentor decided to address this shortcoming of Indian teaching methods even at the IITs which are the best in the country. Hence this Gas Turbine was procured for the benefit of the students. Thanks for your kind words.

This is an amazing explaination. Really appreciate for more video related to entire working of a turbojet engine.

@@aravindm8512 Thanks. Will do so but this may take some time.

Relative to the rotor blades (which are moving).

@@spvmentors7258 so v1 is the difference between absolute velocity of air at the leading edge and the rotor blade. V2 is the difference between absolute air velocity at trailing edge and the rotor blade. Since the rotor blade speed is constant and the velocity of air at the trailing edge woyld've increased a bit (compared to the leading edge air velocity) v2 is lower than v1. Am I getting this correctly??

@@shrirham489 You seem to be partly correct. It is vectorial and not scalar addition/subtraction. V2< V1 because of divergent passages between the rotor blades. So p2>p1. If degree of reaction were zero, p2=p1 and v2=v1.

To understand clearly please see this video (1:58 onward) kzbin.info/www/bejne/iWjaeWawq56cl8U

Chemical energy available in 1litre of Petrol is 32.4Mj/l ,Diesel is 38.7Mj/l , Kerosene is 36.8Mj/l ,Butter is 29.24Mj/l ,Ghee is 33.93 Mj/l ,Wood is 27Mj/l ,Coal is 33Mj/l ,Sugar is 24Mj/l.

Energy available in 1 L of :- 1> Diesel :- 38.67 MJ/L 2> Kerosene :- 36.8 MJ/L 3> Butter :- 29.24 MJ/L 4> Ghee :- 33.93 MJ/L 5> Wood :- 27 MJ/L 6> Coal :- 33 MJ/L 7> Suger :- 23.97 MJ/L 8> Petrol :- 33.75 MJ/L

Chemical energy available in one litre of :- (1) Petrol = 33.75 Mj/L (2) Diesel = 38.7 Mj/L (3) Kerosene = 36.8 Mj/L (4) Butter = 29.24 Mj/L (5) Ghee = 33.93 Mj/L (6) Wood = 27 Mj/L (7) Coal = 33 Mj/L (8) Sugar = 23.97 Mj/L

1.National origin and manufacturer- TV2-117A (Russia, kilmov),HAL HTSE-1200 (India,HAL), Ardiden (France,Sofran Helicopter engines). 2.Compressor- TV2-117A (Ten stage axial flow), Ardiden1 (two stage centrifugal compressor). 3.Dry Weight- TV2-117A (330kg), HAL HTSE-1200(235kg), Ardiden1 (205kg). 4.Turbine- TV2-117A(Four stage free turbine), HAL HTSE-1200(free power turbine), Ardiden1 (two stage free tubine). 5.combustors- TV2-117A (annular flame tube), HAL HTSE-1200(effusion cooled combustors), Ardiden1 (reverse flow annular). 6.Specific Power- TV2-117A(3.39kw/kg), Ardiden1 (4.58-5.03 kw/kg). 7.Air mass flow- TV2-117A(8.1kg/s). 8.Pressure ratio- TV2-117A(6.6:1 at 21200rpm). 9.Max TIT- TV2-117A (880°c).

@@amritpalsingh4622 Please submit hard copy. Inform everyone too.

@@amritpalsingh4622 Later version of TV-2 engine had pressure ratio of 7.3 and max TIT of 925 degrees Celsius.

1.Compressor rotor blades from stage 1 to 3 purpose is to impart kinetic energy to air by increasing its tangential momentum and rotor blades have diverging passages to increase the absolute velocity. Material is steel. 2.Compressor intermediate casing- material is titanium purpose it contains 4 to 9 stages of compression. 3.Compressor rear casing- material is steel purpose it contains 10th stage and exit guide vane and also engine is mounted on it because of the centre of gravity of the engine 4. Diffuser outer shroud- purpose it contains duplex burners and torch ignitors to ignite the fuel coming from duplex burners. 5. Combustion chamber outer casing- purpose it contains annular flame tube of tempered steel it heats the high pressured air from compressor. 6. Blow off valve purpose is to release back pressure to avoid starting problems. 7. Compressor drum purpose the rotor blades are attached to the compressor drum.

1> Compressor rotor blades:- It increase K.E to the air by increasing tangential angle. 2> Compressor stator vanes :- It convert K.E to static pressure or increase pressure. 3>Compressor shaft :- Rotor blade and stator vanes are mounted on it. 4> Compressor intermediate casing :- It contains 4 to 9 stage of rotor and stator blades. 5> bleed valve :- Its release the back pressure air to prevent chocking. 6> compressor rear casing :- It contain 10th stage and exist guide vanes, It's material is steel. 7>diffuser outer shroud:- It contain duplex 8 burners and 2 torch ignitors

(1) Compressor rotor blades from 1rst stage to 3rd stage. Its purpose is to impart kinetic energy to air by increasing its tangential momentum and rotor blades have diverging passages to increase the absolute velocity. Its material is steel (2) Compressor intermediate casing = material use in compressor intermediate casing is titanium. Its purpose is to contains 4 to 9 stages of compression. (3) Compressor rear casing = material use in compressor rear casing is steel. Its purpose is to contains 10th stage and exit guide vane and also engine is mounted on it because of the centre of gravity of the engine. (4) Diffuser outer shroud =Its purpose it contains duplex burners and two torch ignitors to ignite the fuel coming from duplex burners. (5) Combustion chamber outer casing = Its purpose is to contains annular flame tube of tempered steel it heats the high pressured air from compressor. (6) Blow off valve = Its purpose is to release back pressure to avoid starting problems. (7) Compressor drum = Its purpose is, the rotor blades are attached to the compressor drum.

@@Jdnxh8639 Why does absolute velocity increase in rotor blades? Diverging passages should normally reduce the speed when the flow area increases and the flow is subsonic.

@@rohansharma9669 Point No. 1: What do you mean by tangential angle? Point No. 3: Rotor blades are not mounted on the compressor shaft. Stator vanes are also not mounted on the shaft. Point No. 5: When does it prevent chocking? Submit the correct answers again.

1] *_First support housing_* :- In this material is magnesium alloy & Aluminum alloy it's purpose is to support engine. 2] *_Compressor front casing_*:-It's material is titanium and it consist of VIGV, VGV1 ,VGV2 ,VGV3. 3] *_Compressor intermediate casing_*:- It's material used titanium it contains 4 to 9 stages of compression. 4] *_Compressor rear casing_*:- It's Material is steel used to make casing & it contains 10th stage and exit guide vane. 5] *_Diffuser outer shroud_*:- It contains duplex burners and torch ignitors. 6] *_Combustion chamber outer casing_*:- It consist of annular flame tubes. 7] *_Compressor turbine_*:- it consist of 2 stages of NGV & 2 stages of rotor blades. 8] *_Fourth and fifth support housing_*:- it is supports of barings for free turbine. 9] *_Main drive assembly_*:- It's purpose is to drive free turbine via main shaft. 10] *_Speed Governor RO-40_*:- It regulates the speed of shaft.

1. First support housing-Material used is magnesium alloy and its purpose is to support engine. 2.compressor front casing-material used is titanium and it contains vigv(variable inlet guide vain), vgv1 ,vgv2 ,vgv3 . 3.compressor intermediate casing- material used is titanium and it contains 4 to 9 stages of compression which are set of rotor blade and stator vain 4.compressor rear casing- material used is steel and it contains 10th stage and exit guide vane. 5. Diffuser outer shroud- it has duplex burners and torch ignitors attached to it. 6. Combustion chamber outer casing- it contains annular flame tubes. 7. Compressor turbine- it contains 2 sets of ngv and rotor blades in the form of stages. 8. Fourth and fifth support housing- it supports free turbine with bearings. 9.Main drive assembly-it has free turbine via the main shaft that drives the main rotor. 10.Speed governor ro-40- it regulates the speed.

1. First support housing-Material is magnesium alloy purpose is to support rotating shaft. 2.compressor front casing-material is titanium purpose it contains vigv, vgv1 ,vgv2 ,vgv3 . 3.compressor intermediate casing- material is titanium purpose it contains 4 to 9 stages of compression. 4.compressor rear casing- material is steel purpose it contains 10th stage and exit guide vane. 5. Diffuser outer shroud- purpose it contains duplex burners and torch ignitors. 6. Combustion chamber outer casing- purpose it contains annular flame tubes. 7. Compressor turbine- purpose it contains 2stages of ngv and 2stages of rotor blades. 8. Fourth and fifth support housing- it supports free turbine with bearings. 9.Main drive assembly- purpose is free turbine via the main shaft drives the main rotor. 10.Speed governor ro-40- purpose is it regulates the speed.

@@rohansharma9669 First Support Housing has been removed and hence is not seen in the video. Compressor Turbine, Fourth & Fifth Support Housing, Main Drive Assembly and Speed Governor are also not seen in this video. Please see the video at least 3 times again and give the correct answer.

@@amritpalsingh4622 First Support Housing has been removed and hence is not seen in the video. Compressor Turbine, Fourth & Fifth Support Housing, Main Drive Assembly and Speed Governor are also not seen in this video. Please see the video at least 3 times again and give the correct answer.

Diverging passages (cross-sectional flow area is increasing).

Oh thank you very much. Tell her that we do not run this turbine. We just open it sometimes and then try to put all the parts back. Such a simple thing is no where done in our (Indian) Engineering Colleges and Universities that give B.Tech and M.Tech degrees.

So despite the small space, we have created this facility. I studied 'Design of Gas Turbines' at the IIT Madras which is spread over 100s of acres. But during my M.Tech course, all teaching was done on black board. We never touched any jet engine/gas turbine. Thank you for your response.

Delighted to hear from you. Thanks for your kind words.

Thank you very much for your valuable suggestion.

thank you very much.

Thank you very much Dr. Brar.

1. TV-2 has compressor blades made of steel. Titanium alloy may be used. 2. Number of compressor stages can be increased to more than 10 to have higher pressure ratio to improve thermal efficiency. 3. Max TIT is 925 degrees Celsius. Using advanced alloys for making the Turbine NGVs and better cooling techniques, TIT can be increased further thus reducing the BSFC. 4. Better aerodynamic design can lead to higher pressure ratio per stage in the compressor. 5. Stronger and lighter alloys can be used to make the various engine parts thus improving the power to weight ratio. 6. Better design of turbine can lead to greater pressure/temperature drop and reduction in exhaust temperature thus increasing power output and thermal efficiency.

1. TV-2 has compressor blades made of steel. Titanium alloy may be used. 2. Number of compressor stages can be increased to more than 10 to have higher pressure ratio to improve thermal efficiency. 3. Max TIT is 925 degrees Celsius. Using advanced alloys for making the Turbine NGVs and better cooling techniques, TIT can be increased further thus reducing the BSFC. 4. Better aerodynamic design can lead to higher pressure ratio per stage in the compressor. 5. Stronger and lighter alloys can be used to make the various engine parts thus improving the power to weight ratio. 6. Better design of turbine can lead to greater pressure/temperature drop and reduction in exhaust temperature thus increasing power output and thermal efficiency.

Thank you! Cheers!

1. TV-2 has compressor blades made of steel. Titanium alloy may be used. 2. Number of compressor stages can be increased to more than 10 to have higher pressure ratio to improve thermal efficiency. 3. Max TIT is 925 degrees Celsius. Using advanced alloys for making the Turbine NGVs and better cooling techniques, TIT can be increased further thus reducing the BSFC. 4. Better aerodynamic design can lead to higher pressure ratio per stage in the compressor. 5. Stronger and lighter alloys can be used to make the various engine parts thus improving the power to weight ratio. 6. Better design of turbine can lead to greater pressure/temperature drop and reduction in exhaust temperature thus increasing power output and thermal efficiency.

1. TV-2 has compressor blades made of steel. Titanium alloy may be used. 2. Number of compressor stages can be increased to more than 10 to have higher pressure ratio to improve thermal efficiency. 3. Max TIT is 925 degrees Celsius. Using advanced alloys for making the Turbine NGVs and better cooling techniques, TIT can be increased further thus reducing the BSFC. 4. Better aerodynamic design can lead to higher pressure ratio per stage in the compressor. 5. Stronger and lighter alloys can be used to make the various engine parts thus improving the power to weight ratio. 6. Better design of turbine can lead to greater pressure/temperature drop and reduction in exhaust temperature thus increasing power output and thermal efficiency.

1. TV-2 has compressor blades made of steel. Titanium alloy may be used. 2. Number of compressor stages can be increased to more than 10 to have higher pressure ratio to improve thermal efficiency. 3. Max TIT is 925 degrees Celsius. Using advanced alloys for making the Turbine NGVs and better cooling techniques, TIT can be increased further thus reducing the BSFC. 4. Better aerodynamic design can lead to higher pressure ratio per stage in the compressor. 5. Stronger and lighter alloys can be used to make the various engine parts thus improving the power to weight ratio. 6. Better design of turbine can lead to greater pressure/temperature drop and reduction in exhaust temperature thus increasing power output and thermal efficiency.

1. TV-2 has compressor blades made of steel. Titanium alloy may be used. 2. Number of compressor stages can be increased to more than 10 to have higher pressure ratio to improve thermal efficiency. 3. Max TIT is 925 degrees Celsius. Using advanced alloys for making the Turbine NGVs and better cooling techniques, TIT can be increased further thus reducing the BSFC. 4. Better aerodynamic design can lead to higher pressure ratio per stage in the compressor. 5. Stronger and lighter alloys can be used to make the various engine parts thus improving the power to weight ratio. 6. Better design of turbine can lead to greater pressure/temperature drop and reduction in exhaust temperature thus increasing power output and thermal efficiency.

1. TV-2 has compressor blades made of steel. Titanium alloy may be used. 2. Number of compressor stages can be increased to more than 10 to have higher pressure ratio to improve thermal efficiency. 3. Max TIT is 925 degrees Celsius. Using advanced alloys for making the Turbine NGVs and better cooling techniques, TIT can be increased further thus reducing the BSFC. 4. Better aerodynamic design can lead to higher pressure ratio per stage in the compressor. 5. Stronger and lighter alloys can be used to make the various engine parts thus improving the power to weight ratio. 6. Better design of turbine can lead to greater pressure/temperature drop and reduction in exhaust temperature thus increasing power output and thermal efficiency.

1. TV-2 has compressor blades made of steel. Titanium alloy may be used. 2. Number of compressor stages can be increased to more than 10 to have higher pressure ratio to improve thermal efficiency. 3. Max TIT is 925 degrees Celsius. Using advanced alloys for making the Turbine NGVs and better cooling techniques, TIT can be increased further thus reducing the BSFC. 4. Better aerodynamic design can lead to higher pressure ratio per stage in the compressor. 5. Stronger and lighter alloys can be used to make the various engine parts thus improving the power to weight ratio. 6. Better design of turbine can lead to greater pressure/temperature drop and reduction in exhaust temperature thus increasing power output and thermal efficiency.

Q 8 - We can Improve the engine performance by - * Increaseing the pressure ratio by increasing the no. of stages of compressor . * By improving the quality of material used . * By reducing the fuel consumption. * By reducing the exhaust temperature. * By improving the quality of turbine blades . * By increasing the Turbine inlet temperature.

Efficiency of this engine can be improved with these steps mentioned below - 1. By increasing the Turbine Inlet Temperature (TIT). 2. By decreasing the exhaust temperature. (1-T2/T1) 3. By using the fuel which has higher octane number. 4. By increasing the pressure ratio of the engine .

Yes, indeed. Thanks.

Good. For more clarifications you can refer to the part-2 of the video. Part-3 of the video will also be uploaded. kzbin.info/www/bejne/iWjaeWawq56cl8U

You may suggest few more topics. Thanks for recording this video.