title: ÐÐ²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð´Ð»Ñ Ð±ÐµÑÐ¿Ð¸Ð»Ð¾ÑÐ½Ð¾Ð³Ð¾ Ð»ÐµÑÐ°ÑÐµÐ»ÑÐ½Ð¾Ð³Ð¾ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ° Ñ ÑÑÐ³Ð¾Ð¹ 5,5 ÐºÐ
title: Ð²ÑÐ¿ÑÑÐºÐ½Ð°Ñ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ°
titleType: Subtitle
title: Engine for an unmanned aerial vehicle with a thrust of 5.5 kN
Creators: name: ÐÐµÐ±ÐµÐ´ÐµÐ², ÐÑÐµÐ²Ð¾Ð»Ð¾Ð´
Publisher: name: Ð¡Ð°Ð½ÐºÑ-ÐÐµÑÐµÑÐ±ÑÑÐ³ÑÐºÐ¸Ð¹ Ð¿Ð¾Ð»Ð¸ÑÐµÑÐ½Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ½Ð¸Ð²ÐµÑÑÐ¸ÑÐµÑ ÐÐµÑÑÐ° ÐÐµÐ»Ð¸ÐºÐ¾Ð³Ð¾
Year: 2020
Subjects: ÑÑÐ´Ð´
Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÑÑÐ´Ð´-50
Ð±Ð¿Ð»Ð°
ÑÑÐ´Ð´ Ð¼Ð°Ð»Ð¾Ð¹ ÑÑÐ³Ð¸
turbofan engine
gas turbine engine
trdd-50
uav
law-thrust turbofan engine

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description: This final qualification work is dedicated to the design of a small-sized turbojet bypass engine designed for installation on medium-sized unmanned aerial vehicles (UAVs), training and small-sized manned aircraft, and also as a cruising engine for cruise missiles (CM). Small-size small-thrust turbofan engines have been in demand for decades, and this is primarily due to the development of remote piloting technologies for civil and military aircraft. After analyzing the products of domestic manufacturers of gas turbine engines (GTE), we can conclude that the market is experiencing a significant shortage of gas turbine engines of this class. The prototype of the engine under design is the turbine engine TRDD-50 manufactured by ODK- "Saturn" and the Omsk Machine-Building Design Bureau (OMKB). Some design changes were made to this prototype: the last centrifugal compressor stage was replaced by a centrifugal one, the combustion chamber became straight-through, the impeller of the low-pressure turbine has a Christmas-tree lock connection. Graduation work contains: 1. Variant thermal calculation of the parameters of the turbofan engine. Choosing the best option 2. Gas-dynamic calculation of the compressor 3. Gas-dynamic calculation of the combustion chamber 4. Gas-dynamic calculation of the turbine 5. Strength calculations of the rotor of the last stage of the turbine. Vibration diagrams of the working blade. According to the results of the calculation, high power indicators were achieved with a comparable fuel consumption. The relative simplicity of the design and the resulting low cost allow this engine to compete with foreign analogues of this size and power class. For this reason, this work is in demand and relevant.