Unit 2 Aircraft Propulsion J Singh MS Deepa

  • Slides: 15
Download presentation
Unit 2 Aircraft Propulsion J Singh / MS Deepa Aeronautical

Unit 2 Aircraft Propulsion J Singh / MS Deepa Aeronautical

Refresher • Mass Transfer • Reviewed Working of a Gas Turbine Engine • Thrust

Refresher • Mass Transfer • Reviewed Working of a Gas Turbine Engine • Thrust Equation for Turbojet, Turbofan, Turboprop, Ramjet Engine • Quiz • Tutorial posted on “aero 2016” google group – 8 th August, All tutorials will be discussed in the class. Pl work out individually

Ideal (Brayton Cycle) • Compression and Expansion are Reversible and Adiabatic • Change of

Ideal (Brayton Cycle) • Compression and Expansion are Reversible and Adiabatic • Change of KE of working fluid between inlet and outlet of each component is negligible • No pressure losses in the inlet, CC, exhaust ducting, ducting • Working fluid has the same composition throughout the cycle • Perfect gas with constant specific heats • Mass flow of gas is constant throughout the cycle • Heat transfer is complete, so that Temperature rise on cold side equals the temperature drop on hot side

Performance of Gas Turbine Cycles • Forward speed and Altitude • Specific Work output

Performance of Gas Turbine Cycles • Forward speed and Altitude • Specific Work output and Cycle Efficiency depend only on Pressure Ratio and Max Cycle Temperature

Refresher • Tutorial posted on “aero 2016” google group – 8 th August, All

Refresher • Tutorial posted on “aero 2016” google group – 8 th August, All tutorials will be discussed in the class. Pl work out individually • Question papers (class in-charge) • Brayton Cycle: Efficiency & Specific Work output (depend only on…. and…. . )

Cycle Analysis • Heat Exchange • Reheat • Intercooled Numerical (V. Ganesan)

Cycle Analysis • Heat Exchange • Reheat • Intercooled Numerical (V. Ganesan)

Factors affecting Thrust • Velocity • Temperature • Altitude / Pressure Also refer class

Factors affecting Thrust • Velocity • Temperature • Altitude / Pressure Also refer class notes provided

Thrust • • • Propelling Nozzle Outlet: Area (Ae) = Pressure (P 0) =

Thrust • • • Propelling Nozzle Outlet: Area (Ae) = Pressure (P 0) = Mass Flow (W 2) = Velocity (Vj) = 0. 2150 m² 143. 325 k. Pa 101. 325 k. Pa (ISA) 70 kg/s 590 m/s Calculate Thrust (k. N) at Sea Level Static Condition.

Thrust with Reheat • • • Afterburner Propelling Nozzle Outlet: Area (Ae) = 0.

Thrust with Reheat • • • Afterburner Propelling Nozzle Outlet: Area (Ae) = 0. 2900 m² Pressure (Pe) = 136. 325 k. Pa Pressure (o) = 101. 325 k. Pa Mass Flow (W 2) = 70 kg/s Velocity (Vj) = 740 m/s Calculate Thrust (k. N) at Sea Level Static Condition.

Thrust Augmentation • There are occasions when maximum thrust from a basic gas turbine

Thrust Augmentation • There are occasions when maximum thrust from a basic gas turbine engine is inadequate, and some method of increasing the available thrust is required

Afterburning / Reheat This is employed to boost the thrust at various altitudes thus

Afterburning / Reheat This is employed to boost the thrust at various altitudes thus increasing aircraft performance. This is limited to short periods only, such as combat or take-off, due to the increased fuel consumption.

Water / Water-Methanol Injection This is employed to restore, or even boost, the thrust

Water / Water-Methanol Injection This is employed to restore, or even boost, the thrust from a gas turbine operating from hot or high altitude airfields. This method is now normally limited to turboprop powered transport aircraft.

Aircraft engine schemes (1) Turboprop with two stage centrifugal compressor Twin-spool turboprop with axial

Aircraft engine schemes (1) Turboprop with two stage centrifugal compressor Twin-spool turboprop with axial compressor

Aircraft engine schemes (2) Single spool turbojet with axial compressor Turboshaft with twin-spool gas

Aircraft engine schemes (2) Single spool turbojet with axial compressor Turboshaft with twin-spool gas generator Twin-spool bypass

Aircraft engine schemes (3) Triple spool turbofan (separate exhausts) Unducted (aft)fan or propfan

Aircraft engine schemes (3) Triple spool turbofan (separate exhausts) Unducted (aft)fan or propfan

UNIT 1 Aircraft Propulsion Jitendra Singh MS DeepaUNIT 1 Aircraft Propulsion Jitendra Singh MS Deepa
Electric Propulsion Electric Propulsion 3 Propulsion Propulsion ReferenceElectric Propulsion Electric Propulsion 3 Propulsion Propulsion Reference
Rocket Propulsion Types of Propulsion Systems All propulsionRocket Propulsion Types of Propulsion Systems All propulsion
AIRCRAFT AIRWORTHINESS AIRCRAFT AIRWORTHINESS WHAT IS AIRWORTHY AIRCRAFTAIRCRAFT AIRWORTHINESS AIRCRAFT AIRWORTHINESS WHAT IS AIRWORTHY AIRCRAFT
Aircraft Maintenance Engineering Aircraft Law 1 02 AircraftAircraft Maintenance Engineering Aircraft Law 1 02 Aircraft
Aircraft Unit Load Devices 2016 05 0310 AircraftAircraft Unit Load Devices 2016 05 0310 Aircraft
Propulsion Workshop InSpace Propulsion Technology Area 02 AlfredPropulsion Workshop InSpace Propulsion Technology Area 02 Alfred
AME 436 Energy and Propulsion Lecture 11 PropulsionAME 436 Energy and Propulsion Lecture 11 Propulsion
Rocket Propulsion Microsoft Encarta Rocket Propulsion So FRocket Propulsion Microsoft Encarta Rocket Propulsion So F
Chapter VI Propulsion of Ships The propulsion systemChapter VI Propulsion of Ships The propulsion system
Nuclear Propulsion Basics Dr Andrew Ketsdever Nuclear PropulsionNuclear Propulsion Basics Dr Andrew Ketsdever Nuclear Propulsion
AME 436 Energy and Propulsion Lecture 14 PropulsionAME 436 Energy and Propulsion Lecture 14 Propulsion
Propulsion Preliminary Design Review Phoenix Aerospace Propulsion TeamPropulsion Preliminary Design Review Phoenix Aerospace Propulsion Team
Nuclear Thermal Propulsion NTP In Space Propulsion DemoNuclear Thermal Propulsion NTP In Space Propulsion Demo