ISSN: 2320-2459

Reach Us
+44-1522-440391

All submissions of the EM system will be redirected to **Online Manuscript Submission System**. Authors are requested to submit articles directly to **Online Manuscript Submission System** of respective journal.

Mahatma Gandhi University, Kottayam, Kerala, India

- *Corresponding Author:
- Christine Cherian

Mahatma Gandhi University

Kottayam

Kerala, India

**Tel:**+91 9207116957

**E-mail:**christincherian12@gmail.com

**Received date:** 09/17/2018; **Accepted date:** 02/01/2019; **Published date:** 02/08/2019

**Visit for more related articles at** Research & Reviews: Journal of Pure and Applied Physics

This is an eye-opening study on the overall efficiency of a jet generating motors on the basics of ambient conditions of compressor which produces high environmental condition for effective combusting. In general the efficiency of a gas turbine version of jet production is taken for studying and finding the changes of efficiency that happens on the basics of changing ambient condition on compressor. Let taking the primary and secondary compressor of modern version of gas turbine engine, for studying the variation of overall efficiency on the basics of ambient and providing physical conditions and establishing a general picture of combinations of compressor and its effects on the overall efficiency. Over here, we have two set of compressors were available for producing compression, such as low pressure and high pressure (this is based on the pressure has been used as the initial and provided by compressor, to the air molecule which present on the compressor). This can be defining the nature of the compressor. That is, if the compressor work with low pressure air as inlet and provide comparatively lower compression to the molecule, we can be defining it as the low pressure compressor. Similarly, if the compressor works comparatively high environment, it can be calling as high pressure compressor. In this study, Brayton cycle is used as the fundamental cycle for jet production.

Brayton cycle, Efficiency, Work, Temperature

Generally, a modern version of gas turbine engine has two compressors such as low pressure and high pressure. This is on
the basics of the pressure which require and provide to the air molecule. Actually the position of the compressor is indicating the
type. Example, when we place a set of rotating blade at the entry position of air, this has capable to bypass air at low pressure and
provide comparatively low pressure to the incoming air molecule. But, when we placed a rotter blade at before the combusting
chamber, this receive comparatively high pressurized air molecule as inlet and compressors them to high pressure. More precisely
saying, the casing of the compressor causes compression action to the molecule of air and where the role of the moving blade is to
provide sustainable motion to the air molecule for completing its compression. Let analyzing the impact of increasing the number
of compressors and how its affect the overall efficiency of the jet producing motor **(Figure 1)** [1-4].

Considering Brayton Cycle as the fundamental of gas turbine version of jet production and which gives the work and require
heat energy and power of the cycle **(Figure 2)**. In the case of the compressor, it performs adiabatic compression operation and
this niter neither adds nor subtracts heat energy on the process. So, we need to maintain the energy of the system as constant,
for that we race the Values of pressure, temperature and Velocity of the inlet air** (Figures 3 and 4)** [5-9].

Where we race the value of (T^{1}, S^{1} ) as (T^{1}^{′}, S^{1′} ) and similarly the (T^{ 4}, S^{ 2}) (transform to (T ^{4′}, S^{2} ) and we maintain the values of
T ^{2} and T ^{3} (operational values on Combusting chamber).

Where we have three cycles, on first cycle we have T_{1}, T_{2}, T_{3} and T_{4}, in second cycle the T_{1} and T_{4} where transforms to T_{1′} and T_{4 ′} ,
last cycle is a combination of above two cycles. So the work can obtain as

(1)

(2)

(3)

The combination of eqns. (1)-(3) can be define as.

(4)

And their corresponding efficiencies can define as

(5)

(6)

(7)

Usually, the efficiency is the ratio of output and input, where work is consider as output and heat energy is considers as input. So taking the ratio of the work with heat energy, we can obtain it as:

Or

This can be deduce as

Or

The above equation is the general equation of the combination of cycles. This equation can be written as the combination of second and Thread efficiencies by multiplying and dividing on the final term.

Similarly the net efficiency can be written as the combination of first and second efficiency, by multiplying and dividing (T_{4} –
T_{1}) on the second term:

For every the above two equations can equate in the form

Or

Or

All other cases, the efficiency wither

For every constant output temperature, the overall efficiency cannot be change with applying multiple compressors. But, the
output temperature should be fixed. This will give the luxury to every engine manufactures to build multiple compression unite for
effective compression. For every scram jet version of jet production, the second configuration can be applicable. The high pressure
compression on this segment can replace with power compressor unite. That is a pulsed compression and its chances did
not violate the concept of traditional jet production. If we compresses the air molecule in to (P_{2}, V_{2} and T_{2}) (at adiabatic chronology,
we can make effective jets for different operations, such as propel the air craft, lift off the rockets. Launch a missile etc. [10-13].

- Lokanathan S, Gambhir RS (2016) Statistical and Thermal physics. PHI Learning Private Limited Delhi-110 092.
- Upadhyaya JC (2005) Classical mechanics. Himalaya Publication House, Mumbai- 40004
- Prakash S (2015) Mathematical Physics with classical mechanic. Sultan Chand & Sons, New Delhi-110 002, first Edition 1985-86, Fifth and enlarged edition 2006,
- Mathur DS, Bapat MN (2005) Heat and Thermodynamics. Sultan Chand & Sons, New Delhi 110 002.
- www.nasa.gov/missions/research/f_scramjets.html
- www.isro.gov.in/launchers/isros-scramjet-engine-technology-demonstrator-successfully-flight-tested
- https://aviation.stackexchange.com/questions/27020/is-there-a-relationship-between-turbojet-engine-rpm-n1-n2-and-fuel-consumpti
- www.ecourses.ou.edu/cgi-bin/ebook.cgi?doc=&topic=th&chap_sec=09.2&page=theory
- www.slideshare.net/Hamayun14373Liaqat/brayton-cycle-44215461
- www.youtube.com/watch?v=CMFRJ4rGXsc
- www.youtube.com/watch?v=UYMDm4yB1QA&t=466s
- www.youtube.com/watch?v=KjiUUJdPGX0
- www.youtube.com/watch?v=3Y-U7FT7AU4