This paper presents a study of the seal of supporting element in aviation engines with consideration of the mutual influence of its leakage on parameters of internal air system and engine oil system. A method of seal leakage calculation was developed. It connects engine thermogasdynamics calculation, airflow hydraulics calculation and structural analysis of deformed parts. The main sources of heat transferred to the supporting element were determined; their numerical values and percentages for the compressor and turbine were also determined.
This paper provides options of cooling the turbine support for realization of this method. A way of cooling the support determines the quantity of heat supplied to the support. Thus, this article analyzes the sources of heat. Comparison the amount of heat from different sources also is carried out. The amount of heat is defined the temperature of the cooling air. The article provides a comparison of calculation results for different temperatures of the cooling air. After selecting the geometry of the seal system, and determining of the total amount of heat, single seal from the system was researched.
The main purpose of the paper is to explain the design of a single seal as part of whole seal system, which is used to cool the support of the aircraft engine.
1Самарский государственный аэрокосмический университет имени академика С.П. Королёва (национальный исследовательский университет) 2 ОАО «Металлист-Самара» В статье рассматриваются основные источники тепла, поступающего в опору авиационного двига-теля, исследуются способы их определения и даётся их количественное сравнение для определенных условий работы опоры компрессора. На основании определения количества тепла, поступающего от ка-ждого из источников, а также по результатам предварительно выполненного термогазодинамического расчета, выполняются последовательно гидравлический расчёт воздушного охлаждения опоры и вычис-ляется распределение коэффициентов конвективной теплоотдачи и температуры по стенкам опоры дви-гателя. Затем по полученным данным производится структурный тепловой расчёт. В результате струк-турного расчёта определяется распределение температуры в элементах опоры. Приводятся примеры оценки влияния количества тепла, выделяемого различными источниками, а также влияния изменения количества тепла от отдельного источника на уровень потребной прокачки масла через двигатель, при определённой схеме охлаждения опоры. Сравнивается интенсивность теплоотдачи по источникам в за-висимости от режима работы двигателя. На основании предложенной последовательности расчётов была составлена методика определения теплового состояния опоры авиационного двигателя, которая позволит выбирать требуемую систему охлаждения, а также оценить и скорректировать основные параметры мас-ляной системы двигателя.Масляная система, тепловой поток, температура, коэффициент теплоотдачи, трение, уплот-нение, подшипник, эффективность, охлаждение, методика.
Aircraft engines have multiple operation modes for different flight conditions. However, each element of an engine is generally designed for one particular operating mode (maximum load or maximum duration). Mode alteration leads to the variation of pressure and temperature in sealing cavities. Therefore, it is important to consider the full load range into the design process of separate units. This paper presents an original technique of leakage calculation for the spiral-grooved mechanical gas face seal on the different operation modes of the aircraft engine. This type of seal has never used in aircraft engine design. However it has a history of excellent performances in comparison with the traditional type of seals, such as labyrinth or face contact seals. The value of sealing rings deformation must be determined for all operation modes. The flow model of the gas face seal is used to define heat transfer coefficients of seal ring surfaces. Using transient analysis, the influence of the load change rate on the sealing rings can be determined. The developed technique investigates the effect of the engine operating mode alteration on the temperature loads and deformations. Results of the simulation are compared with the experimental data.
The article discusses the possibility of improving the main characteristics (efficiency, specific thrust) of a gas turbine engine by using liquefied natural gas (LNG) as fuel. This possibility is considered on the example of using as fuel instead of aviation kerosene on PS-90A and NK-93 engines. The parameters of the engine were determined at various stages in the cruise flight mode when operating on kerosene and LNG. The parameters evaluating the fuel consumption of the engine are calculated and compared for both fuels. The performance characteristics for kerosene and LNG were evaluated in the system of the Tu-330 subsonic transport aircraft. Energy losses during storage of cryogenic fuel on board the aircraft are estimated.
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