SU325902A1 - Method of simulation of flight conditions of by-pass engine - Google Patents
Method of simulation of flight conditions of by-pass engineInfo
- Publication number
- SU325902A1 SU325902A1 SU6200714286A SU714286A SU325902A1 SU 325902 A1 SU325902 A1 SU 325902A1 SU 6200714286 A SU6200714286 A SU 6200714286A SU 714286 A SU714286 A SU 714286A SU 325902 A1 SU325902 A1 SU 325902A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- engine
- flight conditions
- simulation
- pass engine
- exhaust gases
- Prior art date
Links
Landscapes
- Testing Of Engines (AREA)
Description
Изобретение относитс к области газотурбостроени .This invention relates to the field of gas turbine construction.
Известны способы имитации полетных условий двухконтурного турбореактивного двигател путем подвода выхлопных газов другого двигател на его вход.Known methods of simulating the flight conditions of a double-circuit turbojet engine by supplying the exhaust gases of another engine at its entrance.
Предложенный способ отличаетс тем, что выхлопные газы отбирают от выходного устройства испытуемого двигател .The proposed method is characterized in that the exhaust gases are taken from the output device of the engine under test.
Это позвол ет повысить эффективность установки.This makes installation more efficient.
На фиг. 1 показана схема установки, реализующей предложенный способ; на фиг. то же, без автономной воздуходувки.FIG. 1 shows the installation scheme that implements the proposed method; in fig. the same without an autonomous blower.
Установка содержит испытуемый двух- контурный двигатель 1, двухканальньтй диффузор 2, внутренний канал которого сообщает затурбинное пространство двигател с атмосферой. Наружный контур двигател 1 при помощи наружного канала диф- фузора 2 и турбопривода 3 подключен к основной магистрали 4, подвод щей воздух из автономной воздуходувки через подогреватель на вход двигател 1. При отсутствии автономной воздуходувки (см. фиг.2) The installation contains the tested dual-circuit engine 1, a two-channel diffuser 2, the internal channel of which communicates the turbine space of the engine with the atmosphere. The outer contour of the engine 1 by means of the outer channel of the diffuser 2 and the turbo drive 3 is connected to the main line 4, supplying air from the autonomous blower through the heater to the engine inlet 1. In the absence of the autonomous blower (see figure 2)
внешний кольцевой канал приемного устройства на выходе из двигател выполн ют в виде эжектора, в котором к потоку наруж кого контура подмешиваетс воздух из ат мосферы и некотора часть выхлопных газовThe outer annular channel of the receiving device at the outlet of the engine is made in the form of an ejector, in which air from the atmosphere and some of the exhaust gases are mixed into the flow of an external circuit.
Необходимый расход воздуха и средний уровень температуры на входе в двигатель достигаетс соответствующим подбором расходов смешиваемых потоков. Регулирование уровн наддува обеспечиваетс изменением напорности воздуходувки (см. фиг. 1) либо перепуском части сжатого воздуха в атмосферу перед двигателем (см. фиг. 2). При отсутствии автономной воздуходувки давление наддува будет ниже.The required air flow and the average level of the temperature at the engine inlet is achieved by appropriate selection of the flow rates of the mixed flows. Regulation of the boost level is provided by changing the pressure of the blower (see Fig. 1) or by passing some of the compressed air into the atmosphere before the engine (see Fig. 2). In the absence of an autonomous blower, the boost pressure will be lower.
Claims (1)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU6200714286A SU325902A1 (en) | 1962-01-15 | 1962-01-15 | Method of simulation of flight conditions of by-pass engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU6200714286A SU325902A1 (en) | 1962-01-15 | 1962-01-15 | Method of simulation of flight conditions of by-pass engine |
Publications (1)
Publication Number | Publication Date |
---|---|
SU325902A1 true SU325902A1 (en) | 1977-09-05 |
Family
ID=20437183
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU6200714286A SU325902A1 (en) | 1962-01-15 | 1962-01-15 | Method of simulation of flight conditions of by-pass engine |
Country Status (1)
Country | Link |
---|---|
SU (1) | SU325902A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2622588C1 (en) * | 2016-06-06 | 2017-06-16 | Акционерное общество "ОДК-Авиадвигатель" | Testing bench for gas generators of turbojet bypass engines |
-
1962
- 1962-01-15 SU SU6200714286A patent/SU325902A1/en active
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2622588C1 (en) * | 2016-06-06 | 2017-06-16 | Акционерное общество "ОДК-Авиадвигатель" | Testing bench for gas generators of turbojet bypass engines |
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