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)

Turbulence measurements by means of a fast-response pressure probe

One of possible methods of using a fast-response pressure probe for measuring turbulent flow parameters is described. Recommendations on the probe calibration related to limit of the method’s applicability by Reynolds number (Re) of the flow and confidence frequency range of velocity pulsations by Strouhal number for a probe of this type are provided. Results of measuring turbulent flow parameters using the fast-response pressure probe and a thermal anemometer at different values of Reynolds number in range Re = (1…6)×104 (Re number is defined for the typical size of 10 mm) are compared.

Keywords: fast-response pressure probe, thermal anemometer, turbulence, Reynolds number, Strouhal number

Nepomnyashchiy A.D., Maslov V.P.

Emission assessment of supersonic aircraft engines

The paper presents results of computational and analytical estimation for emission of NOx, CO, HC, nonvolatile particulate matter (nvPM) and smoke (SN) for two turbofan engines, which are considered as advanced engines for supersonic civil aircraft (SCA). For the first engine, the NOx emission near the airport (SLTO) and in the cruise flight with Мf=1,8 was calculated using the engine’s internal parameters. Possibility of using standard subsonic LTO thrust settings in such calculations is estimated for potential engines of next generation SCA. For the second engine based on the CFM56-7B core, a similar analysis was carried out for CO, HС, and partially for nvPM and SN emissions using ICAO engine emission database. All assessments are compared with existing ICAO standards for SCA.

Keywords: ICAO standards, supersonic passenger aircraft, emissions, emission index, emission parameter, combustor

Chelebyan O.G., Strokin V.N., Shilova T.V.

Designing a high-pressure compressor for GTU-32 based on 3D-calculation across viscous flow in HPC

Ahigh-pressure compressor (HPC) for a 32 MW gas turbine unit is designed based on HPC of a 25 MW gas turbine unit. Compared to the prototype, the airflow rate of the HPC is increased by 15 kg/s, pressure ratio is increased by 0,3, and efficiency – by 2%.

Keywords: gas turbine unit, high-pressure compressor, diffuseness, total pressure rate, efficiency

Kozhemyako P.G., Mileshin V.I., Fateev V.A.

Thermomechanical model of gas-turbine engine structure

The paper examines key issues of creating thermomechanical model of a gas-turbine engine structure, which is considered an element of its digital twin. Main provisions, structural correlations and levels of detail of the developed model are described. An example of using the model to determine radial clearances in a high-pressure compressor of a bypass engine is provided, which considers effect of non-axisymmetric loads and deformation of its structure and supports.

Keywords: thermomechanical model, digital twin, numerical simulation, gas-turbine engine, radial clearance

Temis Yu.M., Selivanov A.V., Yakushev D.A.

Design of an axial compressor aerodynamics

This paper considers axial multi-stage compressor’s parameters, their mutual relations and ranges as applied to aerodynamic design. Two different designs of an 8-stage 16.5:1 pressure ratio compressor are compared. Design approaches include: moderate aerodynamic loading, controlled reaction, repeating stages, insensitivity to radial clearance, variability of VSV control.

Keywords: multi-stage axial compressor, pressure ratio, adiabatic efficiency, degree of reaction

Startsev A.N.

Features of developing and selecting characteristics of electrically driven GTE lubrication systems

Principles of developing and selecting characteristics of electrically driven lubrication system for a gas turbine engine are considered in this paper. The effect of gas content in the working medium on the necessary hydraulic power of oil pumps is investigated. An approach to creating dynamic mathematical model of a lubricant system that considers gas content is presented.

Keywords: «electric» gas turbine engine, automatic control system, lubrication system, electric drive, two-phase flow

Gurevich O.S., Gulienko A.I., Schurovskiy Yu.M.