Stoichiometric Gas Turbine Engines

The development of stoichiometric gas turbine engines is associated with solving the problem of high gas temperatures before turbine blades. Currently, these temperatures are in the range of 2 000 K that is lower than the fuel energy capacity. Bringing gas temperatures in gas turbine engines to the level of fuel energy capacity is a strategic task that emerged as soon as the gas turbine engine was first developed and has remained so for more than 80 years. Original methods for cooling the turbine are proposed, that in combination with existing blade manufacturing technology, can provide a solution to this problem. Based on the original technical solutions proposed by the author, a concept of constructing supersonic and hypersonic gas turbine engines is formulated, namely, single-duct single-shaft turbo-jet engines with a high-temperature (more than 2 300 K) regulated single-stage turbine. Different implementations of the concept are proposed, and problem areas are outlined. The emergence of stoichiometric gas turbine engines was to be expected, and it has now been conceptualized. They clearly surpass all known turbo-jet engines, including F-135, and in the future may replace bypass turbojet engines, including those with an afterburner.

References

[1] Raboty vedushchih aviadvigatelestroitel’nyh kompaniy po sozdaniyu perspektivnyh aviatsionnyh dvigateley (analiticheskiy obzor) [The work of leading aircraft engine companies to create advanced aircraft engines (analytical review)]. Ed. Skibin V.A., Solonin V.I. Moscow, TSIAM publ., 2004. 424 p.

[2] Teoriia, raschet i proektirovanie aviatsionnykh dvigatelei i energeticheskikh ustanovok [Theory, calculation and design of aircraft engines and power plants]. Ed. Sosunov V.A., Chepkin V.M. Moscow, MAI publ., 2003. 688 p.

[3] Pis’mennyi V.L. Teploobmennik [Heat Exchanger]. Patent RF no. 2607916, 2017. 8 p.

[4] Pis’mennyi V.L. Vozdukho-vozdushnyi radiator i sposob povysheniia ego effektivnosti [Air-to-air radiator and way to improve its efficiency]. Patent RF no. 2632561, 2017. 6 p.

[5] Pis’mennyi V.L. Sposob okhlazhdeniia turbinnykh lopatok gazoturbinnogo dvigatelia [Method for cooling turbine blades of a gas turbine engine]. Patent RF no. 2409745, 2011. 5 p.

[6] Pis’mennyi V.L. Aviatsionnaia silovaia ustanovka i sposob ee regulirovaniia [Aircraft power plant and method of its regulation]. Patent RF no. 2616089, 2017. 13 p.

[7] Pis’mennyi V.L. Aviatsionnaia stekhiometricheskaia silovaia ustanovka i sposob ee regulirovaniia [Aviation stoichiometric power plant and method of its regulation]. Patent RF no. 2612482, 2017. 12 p.

[8] Pis’mennyi V.L. Sposob forsirovaniia turboreaktivnogo dvigatelia [Method for boosting the turbojet engine]. Patent RF no. 2616137, 2017. 10 p.

[9] Pis’mennyi V.L. Kamera sgoraniia aviatsionnogo gazoturbinnogo dvigatelia [Combustion chamber of an aviation gas turbine engine]. Patent RF no. 2612449, 2017. 5 p.

[10] Fomin V.N., Egorov I.N. Uproshchennaia metodika rascheta kharakteristik osevykh mnogostupenchatykh nereguliruemykh kompressorov [Simplified methodology for calculating the characteristics of axial multistage uncontrolled compressors]. Protsessy i kharakteristiki aviatsionnykh dvigatelei. Sb. Nauchno-metodicheskih materialov [Processes and characteristics of aircraft engines. Collection Scientific and methodical materials]. Moscow, VVIA im. N.E. Zhukovskogo publ., 1987, pp. 121–127.

[11] Pis’mennyy V.L. Pryamotochnyy vozdushno-reaktivnyy dvigatel’ [Ramjet engine]. Patent RF no. 2647919, 2018. 5 p.