Recent developments of axial flow compressors under transonic flow conditions

Srinivas, G; Raghunandana, K; Shenoy, Bhaskar

doi:10.1088/1757-899x/197/1/012078

Cited by 3 publications

(3 citation statements)

References 21 publications

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“…However with the advanced high computational facility and through updated turbulence solvers it is possible to enhance compressor flow simulation performance. The modern computational solvers and recent trends in axial flow compressor under transonic flow conditions are well discussed by Srinivas [15]. Using the above cited equations under the transonic flow conditions the complete flow domain boundary conditions are calculated.…”

Section: Understanding the Flow Domain Boundary Layer Of The Compressmentioning

confidence: 99%

Flow blockage in a transonic axial flow compressor: simulation analysis under distorted conditions

Srinivas

Raghunandana

Shenoy

2018

IJET

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Today the aircraft industry is looking for faster and safer engines for both civil and military applications. The performance of all different types of air breathing engines depends on the amount of mass flow rate of air entering and hot gas ejecting out from the engine. Thrust is the key role for any engine performance. To achieve more thrust all the turbo machinery components like axial fan, axial flow compressor and axial flow turbine should function effectively. This paper is primarily dealing about one of the turbo machinery component, axial flow compressor performance where the study is more focused on flow blockage formation under distorted phenomena. The complete blade boundary layer formation and related flow numerical theory are discussed in detail, accordingly the boundary conditions were set to have better numerical simulations using ANSYS tool. To find the flow blockage formation suitable turbulence model was coded using the well know compressible equations. The flow blockage between the rotor and stator of the compressor stage was calculated and also validated with that of experimental data effectively. The flow simulation results also revealed that the performance parameters under the modern engine transonic speed from Mach 0.8 to 1.2 under the distorted conditions are better for aeromechanical features.

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Section: Understanding the Flow Domain Boundary Layer Of The Compressmentioning

confidence: 99%

Flow blockage in a transonic axial flow compressor: simulation analysis under distorted conditions

Srinivas

Raghunandana

Shenoy

2018

IJET

Self Cite

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“…For the past century a number of literature have been published to analyze the effectiveness of variable guide vanes and bleed air. Bleeds possess the ability for achieving a greater mass flow through front stages of compressor [51][52], [55][56]. The paper is a theoretical based approach.…”

Section: Theoretical Approachmentioning

confidence: 99%

“…For improving the efficiency the designing of an efficient combustion chamber is very crucial because the answer for better efficiency lies in the combustion chamber. The most often used and preferred combustion chamber is the fully annular combustion chamber as it has separate combustion zones and a continuous casing called the annulus [45], [55].…”

Section: Numerical Approachmentioning

confidence: 99%

In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines

Srinivas

2018

IJET

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Today the aircraft engine designing and development work is increasing drastically. Especially aircraft engines play a vital role in order to decide the aircrafts speed and its performance. Broadly turbojet, turboprop, turbo shaft and turbofan engines comes under the category of air breathing engines. Every engine has its own purpose and application. But modern aircrafts require much more advancements. Designing a new aircraft engine has been a really challenging task to the researchers. But giving a complete holistic view of aircraft engines and research gap would definitely help a lot to the new designers. Once identified the drawbacks of engine performance can be corrected in the future. For any new design of aircraft engine researchers are suggested to take Theoretical, Experimental and Numerical approaches. Therefore present paper makes an effort to review complete recent Theoretical, Experimental and Numerical approaches which are followed till date. Under all the three approaches all the air breathing engines have been clearly explained and solicited. The effort is to identify the gaps between different approaches which are hampering the process of engine development. The paper also gives the research gaps that need to be incorporated for effective performance enhancement of the aircraft engines for aeromechanical features.

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Applicability of empirical models of isentropic efficiency and mass flow rate of dynamic compressors to jet engines

Yang

Fang

Zhang

et al. 2019

Progress in Aerospace Sciences

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Recent developments of axial flow compressors under transonic flow conditions

Cited by 3 publications

References 21 publications

Flow blockage in a transonic axial flow compressor: simulation analysis under distorted conditions

Flow blockage in a transonic axial flow compressor: simulation analysis under distorted conditions

In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines

Applicability of empirical models of isentropic efficiency and mass flow rate of dynamic compressors to jet engines

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