I’m not even in college yet but due to the complexity of this subject, I’m getting a head start so I can comprehend and use it to my ability in the future when I am
This is really great sir. I have a problem from an exam about jet engine, can you help me solve it. I have tried a lot of calculations but cant come up with the answer.
375m/s or mach 1.102 pretty good engine at that rate of dry thrust at sea level ....your mach number is lower because you calculated at a value NOT at sealevel with a csubp of 1.025
turbine ... saltine valvoline ... machine ... not turban turbine ... een like machine .. a turban is something you stick on your head to denote religious affiliation ... whcih has NOTHING to do with a jet engine. . first rule of education enunciate words properly .... or else what you taught is for naught
Air with the following properties enter the compressor of an aircraft gas turbine. P=5.45psia T=4300R V=600fps M=150 lbm/sec Thecross-sectionalare(ft2 Please solve this question.
Use equation: Massflowrate=Density x Area x Velocity PV=mRT ; m/v=Density Density = P/RT then substitute Massflowrate=(P/RT)xAreaxVelocity Check units thus, A=73.06ft2 Note: R(air) = approx. 53.34 ft-lbf/lbm-R
Failed exam because of calculator errors, yet these workout is pure gold. If only you were my teacher , I love your consistency
I’m not even in college yet but due to the complexity of this subject, I’m getting a head start so I can comprehend and use it to my ability in the future when I am
This will save your ass. Thermodynamics is one of the hardest topics that exist - being able to do this will save ur ass
2nd year mecheng
Thank you sir, great explanation 🙏🇮🇳
Awesome content! thank you sir!
Thanks! I'm reviewing for a technical interview.
Thank you ❤
This is really great sir. I have a problem from an exam about jet engine, can you help me solve it. I have tried a lot of calculations but cant come up with the answer.
good
Why did you drop mass in your KE equation to get vel? [KE = (1/2)*mass*vel^2]
habit. I often work on per-unit-mass basis. then ke = 1/2 vel^2
Thank you
375m/s or mach 1.102 pretty good engine at that rate of dry thrust at sea level ....your mach number is lower because you calculated at a value NOT at sealevel with a csubp of 1.025
turbine ... saltine valvoline ... machine ... not turban turbine ... een like machine .. a turban is something you stick on your head to denote religious affiliation ... whcih has NOTHING to do with a jet engine.
.
first rule of education enunciate words properly .... or else what you taught is for naught
هل من مصل على النبي محمد صل الله عليه وسلم وبارك الصلاة الإبراهيمية
turbin
Air with the following properties enter the compressor of an aircraft gas turbine.
P=5.45psia
T=4300R
V=600fps
M=150 lbm/sec
Thecross-sectionalare(ft2
Please solve this question.
Use equation:
Massflowrate=Density x Area x Velocity
PV=mRT ; m/v=Density
Density = P/RT then substitute
Massflowrate=(P/RT)xAreaxVelocity
Check units thus,
A=73.06ft2
Note: R(air) = approx. 53.34 ft-lbf/lbm-R
@@xavierramirez6183 thanks