🧊Thermodynamics II Unit 12 – Gas Turbines & Jet Propulsion Systems

Key Concepts and Principles

• Gas turbines convert chemical energy from fuel into mechanical energy through combustion
• Operate on the Brayton cycle, an open, continuous combustion cycle
• Consist of three main components: compressor, combustion chamber, and turbine
• Compressor increases pressure and temperature of incoming air
• Combustion chamber mixes compressed air with fuel and ignites the mixture
  • Combustion process significantly increases temperature and volume of gases
• Turbine extracts energy from hot, high-pressure gases to drive the compressor and output shaft
• Exhaust gases are expelled at a higher velocity than inlet air, producing thrust in jet engines
• Efficiency depends on factors such as compression ratio, turbine inlet temperature, and component efficiencies

Types of Gas Turbines

• Single-shaft gas turbines have compressor, turbine, and output shaft on a single shaft
  • Commonly used in power generation and mechanical drive applications
• Multi-shaft gas turbines have separate shafts for compressor, power turbine, and output shaft
  • Allows for greater operational flexibility and improved part-load efficiency
• Aeroderivative gas turbines are derived from aircraft jet engines and adapted for industrial use
  • Compact, lightweight, and offer high power-to-weight ratios
• Industrial gas turbines are designed specifically for stationary power generation and mechanical drive applications
  • Larger, heavier, and optimized for longer continuous operation
• Microturbines are small-scale gas turbines with power outputs ranging from 30 to 1,000 kW
  • Used in distributed power generation and combined heat and power (CHP) applications

Jet Propulsion Basics

• Jet propulsion is the principle of generating thrust by ejecting a high-velocity fluid
• In jet engines, thrust is produced by accelerating a mass of air using a gas turbine
• Thrust is defined as the product of mass flow rate and velocity change, as per Newton's second law of motion
  • $Thrust = \dot{m} (v_e - v_0)$, where $\dot{m}$ is mass flow rate, $v_e$ is exhaust velocity, and $v_0$ is inlet velocity
• Specific impulse ($I_{sp}$) is a measure of jet engine efficiency, representing thrust per unit mass flow rate of propellant
  • $I_{sp} = \frac{Thrust}{\dot{m}g}$, where $g$ is gravitational acceleration
• Ramjets and scramjets are types of jet engines that rely on high vehicle speed for compression
  • Ramjets operate at supersonic speeds (Mach 1-5), while scramjets operate at hypersonic speeds (Mach 5+)

Thermodynamic Cycles

• Gas turbines operate on the Brayton cycle, an open, continuous combustion cycle
• Ideal Brayton cycle consists of four processes: isentropic compression, isobaric heat addition, isentropic expansion, and isobaric heat rejection
  • In reality, compression and expansion processes are non-isentropic due to irreversibilities
• Thermal efficiency of the Brayton cycle depends on compression ratio and specific heat ratio of the working fluid
  • $\eta_{th} = 1 - \frac{1}{r_p^{(\gamma-1)/\gamma}}$, where $r_p$ is the pressure ratio and $\gamma$ is the specific heat ratio
• Combined cycle power plants integrate a gas turbine (Brayton cycle) with a steam turbine (Rankine cycle) to achieve higher overall efficiency
  • Exhaust heat from the gas turbine is used to generate steam for the steam turbine
• Regenerative Brayton cycle incorporates a heat exchanger to preheat compressed air using turbine exhaust, improving cycle efficiency

Components and Their Functions

• Compressor: Increases pressure and temperature of incoming air
  • Axial compressors are commonly used in gas turbines, consisting of multiple stages of rotating blades and stationary vanes
  • Centrifugal compressors are used in smaller gas turbines, utilizing centrifugal force to compress air
• Combustion Chamber: Mixes compressed air with fuel and ignites the mixture
  • Can-annular combustors consist of multiple individual combustion cans arranged around the engine
  • Annular combustors have a single, continuous combustion zone around the engine
• Turbine: Extracts energy from hot, high-pressure gases to drive the compressor and output shaft
  • Consists of multiple stages of rotating blades and stationary nozzles
  • High-temperature materials and cooling techniques are critical for turbine durability
• Fuel System: Delivers fuel to the combustion chamber at the required pressure, temperature, and flow rate
  • Includes fuel pumps, valves, filters, and injectors
• Lubrication System: Provides lubrication and cooling for bearings, gears, and other moving parts
  • Uses oil as the lubricant, with pumps, filters, and heat exchangers to maintain oil quality and temperature
• Control System: Monitors and regulates engine operation to ensure safe, efficient, and reliable performance
  • Includes sensors, actuators, and electronic control units (ECUs) to manage fuel flow, air flow, and other parameters

Performance Analysis

• Gas turbine performance is evaluated using key parameters such as power output, thermal efficiency, specific fuel consumption, and exhaust gas temperature
• Power output depends on factors such as mass flow rate, turbine inlet temperature, and component efficiencies
  • $Power = \dot{m}c_p(T_3 - T_4)$, where $\dot{m}$ is mass flow rate, $c_p$ is specific heat capacity, $T_3$ is turbine inlet temperature, and $T_4$ is turbine outlet temperature
• Thermal efficiency is the ratio of useful work output to heat input
  • $\eta_{th} = \frac{Power}{Q_{in}}$, where $Q_{in}$ is the heat input from fuel combustion
• Specific fuel consumption (SFC) is the fuel flow rate per unit power output, a measure of fuel efficiency
  • $SFC = \frac{\dot{m}_{fuel}}{Power}$, where $\dot{m}_{fuel}$ is the fuel mass flow rate
• Exhaust gas temperature is a critical parameter affecting turbine life and overall engine performance
  • Higher temperatures improve efficiency but increase thermal stress on components
• Off-design performance analysis evaluates engine behavior under varying operating conditions (altitude, ambient temperature, load)
  • Component maps and performance curves are used to predict off-design performance

Efficiency and Optimization

• Improving gas turbine efficiency involves optimizing cycle parameters, component designs, and operating conditions
• Increasing turbine inlet temperature (TIT) is a key strategy for improving efficiency
  • Advanced materials, thermal barrier coatings, and cooling techniques enable higher TITs
  • Every 50°C increase in TIT yields a 1-2% improvement in thermal efficiency
• Increasing compression ratio also improves efficiency by reducing the required heat input
  • Optimal compression ratio balances efficiency gains with increased compressor work and complexity
• Recuperation (regeneration) can improve efficiency by preheating compressed air using turbine exhaust
  • Effectiveness of recuperation depends on heat exchanger effectiveness and pressure losses
• Intercooling between compressor stages reduces compressor work and improves overall efficiency
  • Requires additional heat exchangers and increases system complexity
• Advanced combustion technologies (lean premixed combustion, staged combustion) reduce emissions and improve fuel efficiency
• Regular maintenance, including cleaning, inspection, and replacement of components, is essential for maintaining optimal performance over time

Real-World Applications

• Power Generation: Gas turbines are widely used for electricity generation in simple cycle and combined cycle power plants
  • Simple cycle plants use a gas turbine only, while combined cycle plants integrate a steam turbine for higher efficiency
• Mechanical Drive: Gas turbines drive compressors, pumps, and other machinery in industrial applications (oil and gas, petrochemical)
  • Offer high power density, reliability, and operational flexibility compared to other prime movers
• Aviation: Gas turbines (jet engines) are the primary propulsion system for modern aircraft
  • Turbojets, turbofans, turboprops, and turboshafts are common types of aircraft gas turbines
• Marine Propulsion: Gas turbines are used in naval and commercial vessels for main propulsion and auxiliary power
  • Offer high power density, compact size, and quick start-up compared to diesel engines
• Cogeneration (Combined Heat and Power): Gas turbines generate electricity and useful heat simultaneously
  • Exhaust heat is recovered for process heating, district heating, or absorption cooling
• Hybrid Systems: Gas turbines are integrated with other power generation technologies for improved efficiency and flexibility
  • Examples include gas turbine-fuel cell hybrids and gas turbine-solar thermal hybrids