How Gas Turbines Work
- 1. This is a Gas Turbine. How does it work?
- 2. • How Does it Work? • Gas Turbine Components • Gas Turbine Performance • Gas Turbine Applications
- 3. 1) Compression 3)Expansion (Turbine) 2) Combustion Output Shaft Power Output Shaft Power Two Shaft Turbine Engine Single Shaft Turbine Engine
- 4. • Compressor Pumps Air into Combustion Chamber • Fuel in Gaseous or Liquid Spray Form Injected into Combustion Chamber and Burned • Continuously Expanding Combustion Products Directed Through Stationary Airfoils − react against the blades of a turbine wheel, causing the shaft to turn, driving the compressor • Remaining High Energy Gas Can be Used − expansion across a nozzle (propulsion) − expansion across another turbine stage (shaft power)
- 5. Simple Cycle Gas Turbines as Aircraft Engines and Land Based Prime Movers COMBUSTOR AIR IN COMBUSTOR FUEL FUEL AIR IN COMPRESSOR TURBINE EXHAUST GAS OUT POWER OUTPUT COMPRESSOR TURBINE EXHAUST GAS OUT THRUST NOZZLE HIGH VELOCITY JET POWER TURBINE
- 6. • Use One or Multiple Compressors • Have Combustor • Use One or Multiple Turbines to Drive Compressor(s) • Aeroengines Generate Propulsion Either by a Hot Gas Jet, Driven Fan or Propeller, or Combination • Industrial Gas Turbines Generate Mechanical Power Using Turbine Driven by Hot Gas
- 7. 1 2 3 5 7 Brayton Cycle (Simple Cycle Gas Turbine ) Velocity Temperature Pressure Flame Temperature 1 2 3 5 7 Station
- 9. IIndussttrriiaall Engiinee on Skkiid
- 10. 1 2 3 5 7 • Axial or Centrifugal Flow • Axial Flow higher efficiency higher flow more stages • Centrifugal Compressors on smaller engines and some mid-size industrial engines less stages rugged simple • Driven by the Turbine on a Common Shaft • Compressor Uses 2/3 of the Fuel Energy That’s why keeping it efficient (read CLEAN) is so important!
- 11. • Airflow Parallel to Rotor Axis • Air Compressed in “Stages” row of moving blades followed by row of stationary blades (stators) is one stage. ♦ Moving blades impart kinetic energy ♦ stators recover the kinetic energy as pressure and redirect the flow to the next stage at the optimum angle
- 12. • Modern Compressor Designs are Extremely Efficient − gas turbine performance rating depends greatly on the compressor efficiency • High Performance Made Possible by Advanced Aerodynamics, Coatings, and Small Blade Tip Clearances • Even Small Amounts of Deposits on Compressor Blades May Cause Large Performance Losses Inlet Guide Vane Stator Vanes (fixed to case) Rotor Blades(rotating)
- 13. • Also Known as the “Burner” • Must be Compact and Provide “Even Temperature Distribution of Hot Gases to the Turbine • Three Basic Configurations: − annular − can − can-annular 1 2 3 5 7
- 14. Injector Combustor Liner (requires intensive cooling) Shaft
- 15. • Annular − Donut shaped, single, continuous chamber that encircles the turbine • Can-annular − multiple, single burners (“cans”) evenly spaced around the rotor shaft • Silo or Can − One or more combustion chambers mounted external to the gas turbine body
- 16. • Used to introduce fuel into the combustion chamber. • Can be for single or dual fuel • Fuel can be mixed with combustion air either… − in the combustor (standard combustion system) − pre-mixed prior to entering combustor ( lean pre-mix, DLN (dry-low-Nox), DLE (dry low emissions), (SoLoNOx) Dry-Low-NOx injector Pre-Mix Barrel Standard injector Solar Mars Injector Standard vs SoloNOx
- 17. 1 2 3 5 7 • Two Basic Types - Radial and Axial − Almost all industrial Gas Turbines use axial flow turbines • Like the Compressor, Turbine Expansion Takes Place in “Stages” − a row of stationary blades (nozzles) followed by a row of moving blades = one stage.
- 18. Two Stage Axial Turbine Turbine Nozzle Segment Nozzle Rotor Blade Nozzle Rotor Blade rotation rotation • First Stage Turbine Nozzle Sees the Hottest Temperatures − Referred to as TIT (Turbine Inlet Temperature) or TRIT (Turbine Rotor Inlet Temperature) − Modern engines run TRIT as high as 2200 F (some even higher)
- 19. COOLING AIR INLET HOT GAS FLOW COOLING AIR HOT GAS FLOW SHOWER HEAD FILM HOLES Convection Cooling Film Cooling
- 20. TIT TRIT T5 Combustor 1st Nozzle 1st Rotor 1st PT Nozzle Cooling Air Flows All temperatures are considered total.
- 21. Gas Turbine Performance Characteristics
- 22. Gas Turbine Performance vs. Ambient Temperature 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 -20 -10 0 10 20 30 40 50 T amb (deg C) Power, Heat rate HP HR
- 23. Efficiency at Part Load Operation 110 100 90 80 70 60 50 50 60 70 80 90 100 Load (%) Rel. Thermal Efficiency (%) Gas Turbine Thermal Efficiencyη/ηref versus Load P/Pmax (Typical, for 3 arbitrarily selected industrial engines)
- 27. 0 0 HEAD Operational Flexibility Managing Varying Demand 1 UNIT 2 UNITS 3 UNITS IN PARALLEL SITE POWER AT 75F FLOW Operating Points in a Compressor Station
- 29. • Base Load (Continuous Duty) – Designed to operate 6,000-8,000 hrs per year (more or less continuously) • Peak Load – Designed to operate approximately 1,000 hours per year (started during peak power demands, usually about once per day) • Stand-By – Designed to operate less than 1,000 hours per year (started if other systems fail) – A “Standby Duty” unit is operated as a backup to, not in parallel with, a normal source of power. – Typical operation ranges from 50 to 100 hours per year with one start per week.
- 30. • Firing Temperature − Output Power − Exhaust Temperature − Life − Maintenance intervals/Cost of Maintenance TRIT Output Power Exhaust Heat Maintenance Cost Net Cash Flow Maintenance Interval (hrs)
- 31. Base Load, Peak Load and Stand-By Units • Engine Life depends on Firing Temperature (and number of starts*) – Thus, a peak load unit can be fired at higher temperatures without any design changes – Higher Firing Temperature means more power, but shorter engine life. * According to some manufacturers