Development of a gas turbine engine starts with optimization of the working process parameters. Turbine inlet temperature is among the most influential parameters that largely determine performance of an engine. As typical turbine inlet temperatures substantially exceed the point where metal turbine blades maintain reasonable thermal strength, proper modeling of the turbine cooling system becomes crucial for optimization of the engine’s parameters. Currently available numerical models are based on empirical data and thus must be updated regularly. This paper reviews the published information on turbine cooling requirements, and provides an approximation curve that generalizes data on all types of blade/vane cooling and is suitable for computer-based optimization.
TiemstraFS.Design of a semi-empirical tool for the evaluation of turbine cooling requirements in a preliminary design stage. Master’s thesis, 2014, p.147.
2.
KopelevSZ.Cooled gas turbine blades. Moscow: Nauka, 1983, p.146.
3.
BaWWangZLiX, et al. Three-dimensional optimal design of a cooled turbine considering the coolant-requirement change.Open Physics2019; 17: 768–778.
4.
BaWWangX-CLiX-S, et al. Definition of cycle based comprehensive efficiency of a cooled turbine.Energy2019; 168: 601–608.
5.
YoungJBHorlockJH.Defining the efficiency of a cooled turbine.J Turbomach2006; 128: 658–667.
6.
SalpingidouCTsakmakidouDVlahostergiosZ, et al. The effect of turbine blade cooling on the performance of recuperative cycles for gas turbines applications.Chem Eng Trans2017; 61: 1027–1032.
7.
SahuMKSanjayY. Investigation of the effect of air film blade cooling on thermoeconomics of gas turbine based power plant cycle.Energy2016; 115: 1320–1330.
8.
SongYGuC-WJiX-X.Development and validation of a full-range performance analysis model for a three-spool gas turbine with turbine cooling.Energy2015; 89: 545–557.
9.
VassilievVGranovskiyALomakinN.Impact of turbine blade internal cooling on aerodynamic loss. In: Proceedings of the ASME Turbo Expo 2A V02AT38A016, Montreal, Canada, June 15–19, 2015.
10.
HollandMJThakeTF.Rotor blade cooling in high pressure turbines.J Aircr1980; 17: 412–418.
11.
AinleyDG.Internal air cooling for turbine blades: a general design study.Aeronautical Research Council Reports and Memorandum, 1957, pp.3013.
12.
ConsonniS.Performance prediction of gas/steam cycles for power generation. PhD thesis, Princeton University, 1992.
13.
TorbidoniLHorlockJH.A new method to calculate the coolant requirements of a high-temperature gas turbine blade.J Turbomach2005; 127: 191–199.
14.
HorlockJHWatsonDTJonesTV. Limitations on gas turbine performance imposed by large turbine cooling flows. In: Proceedings of ASME TURBOEXPO 2000, Munich, Germany, May 8–11, 2000.
15.
Tara ChandVRavindraKBala PrasadK.Exergy assessment of air film blade cooled combined power cycle plant.Int J Ambient Energy2020; 41: 994–1006.
16.
TaraCVRavindraKBalaPK.Performance augmentation of combined cycle power plant under the control of differing open loop cooling techniques to the gas turbine blades.Int J Ambient Energy2020.
JiangCChenH-p. Study on approximate calculation of cooling air allocation for gas turbine. In: 2009 Asia-Pacific power and energy engineering conference, Wuhan, China, March 27–31, 2009.
19.
YinFTiemstraFSRaoAG.Development of a flexible turbine cooling prediction tool for preliminary design of gas turbines.J Eng Gas Turbines Power2018; 140: 91201.
20.
YinFRaoAGBhatA, et al. Performance assessment of a multi-fuel hybrid engine for future aircraft.Aerosp Sci Technol2018; 77: 217–227.
21.
ShvetsITDybanEP.Air cooling of gas turbine parts. Kiev: Naukova dumka, 1974, p.488.
22.
LiCLiuJ-J. A one-dimensional analytical method for turbine blade preliminary cooling design. In: Proceedings of the ASME Turbo Expo 2C V02CT39A027, Seoul, South Korea, June 13–17, 2016.
23.
LiH-BGuCSongY.Through-flow calculation with a cooling model for cooled turbines. Proc IMechE,Part A: J Power and Energy2015; 229: 862–875.
24.
LiHGuC. Through flow calculations for convective cooled turbines In: Proceedings of the ASME Turbo Expo 2B, Dusseldorf, Germany, June 16–20, 2014.
25.
ZyongLTNesterenkoVG.Designing of shrouded cooled blades for high-temperature and high-pressure turbines.Int Sci J2018; 1: 84–90.
26.
Kuz’michevVSTrofimovAA.Design-point calculations of the main parameters of the aircraft gas turbines and compressors. Kuibyshev: Kuibyshev Aviation Institute, 1990, p.72.
27.
InozemtsevAANikhamkinMASandratskiiVL.Fundamentals of gas turbine engines and power plants designing. Volume 2. Compressors. Combustion chambers. Afterburners. Turbines. Exhaust devices. Moscow: Mashinostroenie, 2008, p.365.
GritsenkoEADanil’chenkoVPLukachevSV, et al. Some issues of aviation gas turbine engines designing. Samara: SNTs RAN, 2002, p.527.
30.
PavlenkoGVVolovAG. Gasdynamic designing of axial gas turbine. Kharkov: National Aerospace University, 2007, p.76.
31.
KholschevnikovKVEminONMitrokhinVT.Theory and calculations of aviation turbomachines. Moscow: Mashinostroenie, 1986, p.432.
32.
KulaginVV. Theory, calculations and designing of aircraft engines and power plants: fundamentals of theory of gas turbine engines. Working process and thermodynamic analysis. Volume 1. Joint operation of engine elements and its performance. Moscow: Mashinostroenie, 2002, p.616.
33.
GrigorievVAZhdanovskiiAVKuzmichevVS. Parameters selection and thermodynamic calculations of aviation gas turbine engines. Samara: Samara State Aerospace University Publishing, 2009, p.202.
34.
DerevyankoAVZhuravlevVAZikeevVV.Fundamentals of aviation turbines designing. Moscow: Mashinostroenie, 1988, p.328.
35.
PotkinAN.Complex approach to designing high-temperature cooled gas turbines for reducing risks and development time. PhD thesis, P. A. Solovyov Rybinsk State Aviation Technical University, 2014, p.134.
36.
ZhangJZhangSWangC, et al. Recent advances in film cooling enhancement: a review.Chin J Aeronaut2020; 33: 1119–1136.
37.
KumarSSinghO.Thermodynamic evaluation of gas/steam combined cycle performance with active controlled film cooling distributed generation andAlternative Energy J2014; 29: 49–60.
