A review of research and development on hydrogen-fueled gas turbine power plants

The article provides an overview of the implemented projects of hydrogen-fueled gas turbine engines used in power plants (GTP). The relevance of using hydrogen as a fuel is due to the limited hydrocarbon energy sources, the negative impact of traditional fuels on the environment, and the insufficient efficiency of “green” energy. All major manufacturers of GTP are more or less developing new or converting existing plants to hydrogen-containing fuel. Based on publications, the experience of companies that have successfully implemented projects of GTP running on hydrogen-containing fuel, as well as their plans for the development in this direction, is analyzed. The main engineering problems solved by the manufacturers of gas turbine plants for their use with hydrogen fuel are considered.

Keywords: gas turbine engine, gas turbine plant, power plant, hydrogen, hydrogen fuel, environmentally friendly energy generation

Semenov S.V., Nikhamkin M.Sh., Plotnikov A.I.

Analytical review of modern trends in foreign high-speed aircraft development

Review of foreign research publications on the development of high-speed aircraft technologies is presented in the article. Priority areas of technology and information about the objects under development are analyzed. It is shown that much attention is paid abroad to fundamental research in fields of gas dynamics (external flow and internal flow of gases), fuel combustion in supersonic flow, and creation of new high-temperature materials and coatings. According to leading foreign experts, creation of a high-speed aircraft with a combined power plant is a relevant and technically feasible direction of development in the near future. The concepts of carriers for high-speed aircraft are examined, as well as information on new facilities used for ground-based wind-tunnel and engine tests.

Keywords: high-speed aircraft, fundamental research, combined power plant, test facility, analytical review

Aref’ev K.Yu.

The progress in aviation engine development can be facilitated by creating highly efficient small power plants

The article is devoted to the critical problem of the shortage of modern domestic aircraft engines. It is shown that the rapid progress in aircraft engine development can be carried out based on small-sized GTEs. Such progress can be ensured by developing small-sized GTEs for aircraft of various purposes based on a unified engine core, as well as creation of gas turbine power plants based on existing small-sized GTEs, which will contribute to the growth of Russian power industry. It is shown that the task is quite achievable in the near future.

Keywords: small-sized GTE, aviation GTE, unified engine core, family of GTEs, aircraft, power plant, gas turbine plant, conversion

Lanshin A.I., Solonin V.I.

On the features of a kerosene-hydrogen combustion chamber of a hybrid gas turbine engine

One of the ways to help reduce the emission of gas turbine engines is the use of hybrid gas turbine engines. In the case under consideration, a hybrid GTE is an engine that has not only a low-pressure turbine on one shaft, but also an electric motor that increases the engine thrust due to the fan. The operation of such GTEs on hydrogen is discussed below which will further alleviate the emission problem.

Keywords: hybrid gas turbine engine, hybrid GTE, combustion chamber, alternative fuel, hydrogen, fuel supply system, NOx emission, dual-fuel combustion chamber

Vasiliev А.Yu., Strokin V.N., Shilova T.V.

Research of propulsion system’s engines for the carrier aircraft of an advanced reusable two-stage aerospace system

Studies carried out in the 1980s have shown that in order to implement near-space exploration programs and to develop further space exploration programs, it is necessary to proceed with creation and commissioning of reusable space transport systems. Studies conducted in Russia in the 1990s showed that two-stage aerospace systems are the most rational of horizontal launch and landing systems. To create such systems for launching payloads into near-Earth orbits, the problem of developing a carrier aircraft’s propulsion system is one of the main ones. The article describes the experience of research in the 1990s – early 2000s aimed at forming the technical configuration of combined propulsion systems for a carrier aircraft of an advanced aerospace system. Research on the use of endothermic hydrocarbon fuel in engines of such propulsion systems is presented; the cooling system, cooling capacity and coke deposition problems are also discribed.

Keywords: combined propulsion system, aerospace system, gas turbine engine, air-breathing engine, turbofan, ramjet air-breathing engine, endothermic fuel, cooling capacity, coke deposition

Lanshin A.I., Sokolova O.V., Shikhman Yu.M., Shlyakotin V.E.

Turbulence decay at various Reynolds numbers

The article presents measurements of a flow’s turbulence intensity in the wind tunnel at CIAM’s test facility at different values of the Reynolds number (at full pressure in the wind tunnel p*0 = 0,2…0,8 bar and reduced velocity l = 0,1…0,5). The measurements were carried out using a thermoanemometer. It is further shown that the rate of turbulence decay, determined by the power law “-5/7”, is not a universal characteristic of turbulence.

Keywords: turbulence, turbulence intensity, turbulence decay, Reynolds number, thermoanemometer

Nepomnyashchiy A.D., Maslov V.P., Suntsov S.V.

Research of parameters and characteristics of the turbine-based combined cycle propulsion system of an advanced high-speed aircraft

The paper presents the study of an operation of the turbine-based combined cycle (TBCC) propulsion system based on a turbofan engine in the class of 1800 kgf take-off thrust and a ramjet engine with subsonic combustion speeds as part of a high-speed passenger aircraft. The analysis was carried out using the developed complex mathematical model that combines mathematical models of an air intake device, turbojet, ramjet and bypass system for excess air. Parameters and characteristics were calculated according to the climb trajectory corresponding to the velocity pressure of 60 kPa. The issues of the TBCC in various operating modes, as well as coordination of the operation of the propulsion system’s elements, are considered. The problem of the effect of the dissociation and recombination of combustion products on the flow of the working process in the TBCC is given attention.

Keywords: turbine-based combined cycle propulsion system, air intake, turbojet, ramjet, combined operation mode

Polev A.S., Grunin A.N., Shlyakotin V.E., Alendar’ A.D.

Development of air-breathing engines for high-speed aviation by combining advances in various areas of science and engineering

The article considers possibilities of using high cooling and work capacities of endothermic fuels, similar to using corresponding properties of cryogenic fuels, based on the analysis of advancements in thermochemistry and their use in improving development methods for combined engines with more advanced thermodynamic cycles than the Brayton cycle traditionally implemented in air-breathing engines. The same results should promote an increase in flight speed of an airplane with hydrocarbon-fueled engines.

Keywords: air-breathing engine, combined engine, endothermic fuel, cryogenic fuel, fuel’s cooling capacity, work of cycle