CIAM
Размер:
A A A
Цвет: C C C
Изображения Вкл. Выкл.
Обычная версия сайта
            
Central Institute of Aviation Motors
Версия для слабовидящих
Противодействие коррупции
Eng 
Array
(
    [0] => Array
        (
            [TEXT] => About the journal
            [LINK] => /en/journal-aircraft-engines
            [SELECTED] => 1
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => P
            [ITEM_INDEX] => 0
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => About the journal
                )

            [DEPTH_LEVEL] => 1
            [IS_PARENT] => 
        )

    [1] => Array
        (
            [TEXT] => Archive
            [LINK] => /en/journal-aircraft-engines/edition
            [SELECTED] => 1
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => P
            [ITEM_INDEX] => 1
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => Archive
                )

            [DEPTH_LEVEL] => 1
            [IS_PARENT] => 
        )

    [2] => Array
        (
            [TEXT] => To the Authors
            [LINK] => /en/journal-aircraft-engines/to-the-authors/
            [SELECTED] => 
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => D
            [ITEM_INDEX] => 2
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => To the Authors
                )

            [DEPTH_LEVEL] => 1
            [IS_PARENT] => 1
        )

    [3] => Array
        (
            [TEXT] => Manuscript Submission Requirements
            [LINK] => /en/journal-aircraft-engines/to-the-authors/manuscript-submission-requirements
            [SELECTED] => 
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => P
            [ITEM_INDEX] => 0
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => To the Authors
                    [1] => Manuscript Submission Requirements
                )

            [DEPTH_LEVEL] => 2
            [IS_PARENT] => 
        )

    [4] => Array
        (
            [TEXT] => Operating procedures for the Authors
            [LINK] => /en/journal-aircraft-engines/to-the-authors/operating-procedures-for-the-authors
            [SELECTED] => 
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => P
            [ITEM_INDEX] => 1
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => To the Authors
                    [1] => Operating procedures for the Authors
                )

            [DEPTH_LEVEL] => 2
            [IS_PARENT] => 
        )

    [5] => Array
        (
            [TEXT] => To the Reviewers
            [LINK] => /en/journal-aircraft-engines/to-the-reviewers/
            [SELECTED] => 
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => D
            [ITEM_INDEX] => 3
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => To the Reviewers
                )

            [DEPTH_LEVEL] => 1
            [IS_PARENT] => 
        )

    [6] => Array
        (
            [TEXT] => Contacts
            [LINK] => /en/journal-aircraft-engines/contacts
            [SELECTED] => 
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => P
            [ITEM_INDEX] => 4
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => Contacts
                )

            [DEPTH_LEVEL] => 1
            [IS_PARENT] => 
        )

    [7] => Array
        (
            [TEXT] => Translation
            [LINK] => /journal/translation/
            [SELECTED] => 
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => D
            [ITEM_INDEX] => 5
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => Translation
                )

            [DEPTH_LEVEL] => 1
            [IS_PARENT] => 1
        )

    [8] => Array
        (
            [TEXT] =>  Eng
            [LINK] => /en/journal-aircraft-engines/
            [SELECTED] => 1
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => D
            [ITEM_INDEX] => 0
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => Translation
                    [1] =>  Eng
                )

            [DEPTH_LEVEL] => 2
            [IS_PARENT] => 
        )

    [9] => Array
        (
            [TEXT] => Rus
            [LINK] => /journal/about-the-journal/
            [SELECTED] => 
            [PERMISSION] => R
            [ADDITIONAL_LINKS] => Array
                (
                )

            [ITEM_TYPE] => D
            [ITEM_INDEX] => 1
            [PARAMS] => Array
                (
                )

            [CHAIN] => Array
                (
                    [0] => Translation
                    [1] => Rus
                )

            [DEPTH_LEVEL] => 2
            [IS_PARENT] => 
        )

)

Concepts of aero engines for advanced civil aircraft

The main critical technologies that need to develop for realization of the possible concepts of aero engines in order to meet the target indicators for advanced civil aircraft and their propulsion systems have been identified. The critical technologies developed at CIAM for advanced aero engines are shown.

Keywords: aero engine, hybrid engine, “electric” engine, propulsion system, civil aircraft, critical technologies.

Gordin M.V., Palkin V.A.

GTE performance deterioration due to ice crystal icing and compensation of this effect by control methods

This paper presents the analysis of the ice crystal icing effect on engine components performance characteristics. These characteristics are adapted for use in the thermogasdynamic mathematical model of a commercial turbofan. Algorithms for various engine control methods are developed and introduced into the turbofan mathematical model. Following controllers are considered: rotors rotational speed, engine pressure ratio and thrust calculated in the on-board engine model. Mathematical modeling has been performed to evaluate engine performance using these algorithms. The possibility of compensating for a thrust rollback, due to engine components performance degradation with icing, and reducing ice accretion by the choice of the engine control method is shown. Based on the simulation results, the influence of control methods on the engine behavior with icing is explained.

Keywords: gas turbine engine, thrust, control, icing, ice crystals.

Gurevich O.S., Smetanin S.A., Trifonov M.E.

Determination of the input pulse value as an amendment to the force from GTE thrust in the test facility (closed) box

The paper reviews the problems of determining the value of the input pulse as an amendment to the measured thrust force for the engine with the attached input lemniscate nozzle in the test facility (closed) box. The technique is proposed for estimating the input pulse value, based on determining the difference in the thrust values of the lemniscate nozzle. These values differ when operation conditions change from condition in infinite space (equivalent to working a nozzle on a standard open facility) to conditions in a limited space of a test facility box. Analysis of the results of aerodynamic certification of the test facility (closed) box is shown that in the presence of detached flows in the box, the correction for the input pulse to the thrust force increases significantly.

Keywords: test facility, test box, gas turbine engine, aerodynamic certification, engine thrust, input pulse amendment.

Klinskiy B.M.

Features of creating a test facility for small-sized aviation engines and power plants based on a climatic test unit

This paper describes the design features of the technological systems of the test facility with climatic test unit for testing small aviation engines and power plants. It also gives examples of non-standard solutions to a number of technical problems that arose during the modernization of the U-376 CIAM test facility. The proposed solutions can be successfully implemented for upgrading existing or creating new facility systems.

Keywords: test facility, climatic test facility, technological system, air circuit, shut-off and control valves, force measuring system.

Zhigunov M.M., Mitrofanov K.E.

Improvement of the method for checking the ground “cold” start of a turbofan with high bypass ratio

The paper presents constructive, technological and system measures implemented at CIAM altitude climatic test facility. These measures provide an improvement in the method for checking the ground “cold” start of a high bypass ratio turbofan. Furthermore, they allow to perform certification tests and increase their reliability.

Keywords: altitude climatic test facility, turbofan, high bypass ratio, ground start, «cold» start.

Vasilev D.L., Egorov I.V., Zhigunov M.M., Narуshkin A.A.

The application of the variable pitch fan blades in the distributed powerplant for advance long-range aircraft for matching takeoff and cruise

Results of study at the choice of rational parameters of the distributed powerplant with variable pitch fan blades for advance long-range aircraft are presented. The estimation of effectiveness of variable pitch fan blades for take-off is carried out. Weight and dimensional characteristics of this distributed powerplant are updated. Its cruise/takeoff thrust and fuel consumption characteristics are determined.

Keywords: distributed powerplant, fan module, variable pitch fan blades, long-range aircraft.

Kalenskii S.M., Morzeeva T.A., Ezrokhi Yu.A.

Empirical models of the resource operating time and the liquid phase coke deposit formation dynamics under the aviation kerosene heating

The systematic experimental study of the aviation kerosene heating up to temperatures of 500…900 K at super­critical pressures in the model fuel channel with walls heating by electric current is described. The experiments were carried out for a wide range of the fuel consumptions and thermal parameters. Based on these experimental results the empirical model of the channel wall overheating caused by coke deposits formation and the mathematical model of the coke thickness dynamics on channel walls in the region of liquid-phase coke deposits formation are developed. For these condition both models allow estimating f heat exchangers parameters during the RT and TS-1 kerosenes heating and the possible operating time before achieving the maximum constructive-permissible temperatures of the fuel channel walls.

Keywords: aviation kerosene, hydrocarbon fuels heating, liquid-phase coke deposit formation, mathematical model, heat exchange.

Shlyakotin V.E., Shikhman Yu.M.

Review of works in the USA and Europe on aero engines for civil aircraft of 2020…2040’s

The current state of aircraft engine building and areas of work on the creation of critical technologies for advanced aero engines abroad are considered. It is shown that the parameters of the cycles and the bypass ratio will be significantly increased and composite materials will be widely used in both in the “cold” and “hot” parts of the turbofan engines of short-term prospect (2020…2025). Taking into account significant progress in the development of components of the electrical system, including the components based on high-temperature superconductivity, various concepts of aircraft with hybrid (turboelectric) and electric propulsion systems are considered for the medium and long term prospects (2030…2040).

Keywords: aero engine, hybrid engine, “electric” engine, civil aircraft, critical technologies, propulsion system.

Palkin V.A.