SU1241805A1 - Loop-type tubular-angular combustion chamber - Google Patents
Loop-type tubular-angular combustion chamberInfo
- Publication number
- SU1241805A1 SU1241805A1 SU843717918A SU3717918A SU1241805A1 SU 1241805 A1 SU1241805 A1 SU 1241805A1 SU 843717918 A SU843717918 A SU 843717918A SU 3717918 A SU3717918 A SU 3717918A SU 1241805 A1 SU1241805 A1 SU 1241805A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- diffuser
- annular
- different
- inner shell
- area
- Prior art date
Links
Landscapes
- Superconductors And Manufacturing Methods Therefor (AREA)
Abstract
ПЕТЛЕВАЯ ТРУБЧАТО-КОЛЬЦЕВАЯ КАМЕРА СГОРАНИЯ, содержавша кольцевой канал, ограничешв й внутренней и наружной обечайками, жаровые трубы, образующие межтрубное пространство с переменной площадью проходного сечени между соседнимн трубами, и кольцевой осерадиальный диффузор, выходное отверстие которого выполнено во внутренней обечайке, отличающа с тем, что, с цель*о снижени потерь полного давлени , выходное отверстие диффузора имеет площадь, составл ющую 1,5-2,5 минимальной площади проходного сечени межтрубногр П1юстранства'на его участке, расположенном напротив отверсти .An inlet loop-annular combustion chamber containing an annular channel, limited inner and outer shells, flame tubes forming an annular space with a variable area of the flow area between adjacent pipes, and an annular axial radial diffuser, the outlet opening of which is formed in the inner shell differing in a different diffuser, and the annular diffuser, which had an outgoing opening in the inner shell, which had a different diffuser, and the annular diffuser, which had an outgoing opening in the inner shell, which had a different diffuser, and the annular diffuser, which had an outgoing opening in the inner shell, which had a different diffuser, and the annular diffuser, which had a discharge outlet that differed in the inner circumferential section, had a different diffuser; that, in order to reduce the total pressure loss, the outlet of the diffuser has an area of 1.5-2.5 times the minimum cross-section area of the interstitial pipe its site, located opposite the hole.
Description
: А : BUT
7 87 8
фие./Fie. /
Изобретение относитс к области двигателестроени , в частности к петлевым трубчато-кольцевым камерам сгорани газотурбинных двигателей.FIELD OF THE INVENTION The invention relates to the field of engine construction, in particular to loop-back tubular-annular combustion chambers of gas turbine engines.
Целью изобретени вл етс снижение потерь полного давлени .The aim of the invention is to reduce total pressure loss.
На фиг. 1 показана петлева трубчато-кольцева камера сгорани , продольный разрез; на фиг. 2 - вид по стр-Лкё А на фиг.1FIG. 1 shows a loop-back tubular-annular combustion chamber, a longitudinal section; in fig. 2 is a view of p. Lk A of FIG.
Камера сгорани содержит кольцевой канал 1, ограниченный внутренней и наружной обечайками 2 и 3, жаровые трубы 4, образующие межтрубное пространство с переменной площадью проходного сечени между соседними трубами, и кольцевой осерадиадГьный диффузор 5, В1 одное. отверстие 6 которого выполнено во внутренней обечайке 2 и инее площадь, составл ющую 1,5-. ,5 минималъной площади проходного сечени 7 межтрубного пространства на его участке, расположенном напротив отверсти 6. В стенках жаровых труб 4 выполнены отверсти 8The combustion chamber contains an annular channel 1, bounded by the inner and outer shells 2 and 3, flame tubes 4, which form an annular space with a variable cross-section area between adjacent tubes, and an annular radial diffuser 5, B1 one. the opening 6 of which is made in the inner shell 2 and a frost area of 1.5. , 5 minimum area of the annulus 7 through the annular space in its section located opposite the opening 6. In the walls of the flame tubes 4 there are holes 8
дп подвода воздуха.dp air supply.
При работе камеры сгорани воздух через осерадиальный диффузор 5 поступает в кольцевой канал I и растекаетс далее в межтрубном пространстве,When the combustion chamber is in operation, the air through the osseradial diffuser 5 enters the annular channel I and spreads further in the annular space,
где поток воздуха, частично протека в радиальном направлении через проходное сечение 7 межтрубного пространства , разворачиваетс и продолжает движение в осевом направлении вwhere the air flow, partially flowing in the radial direction through the annulus 7 through the annulus, turns and continues to move in the axial direction in
сторону, прбтивоположную Направлению движени воздуха на входе в осерадиальный диффузор 5. Из межтрубного пространства врздух через отверсти 8 в стенках жаровых труб 4 поступаетthe direction which is opposite to the Direction of air movement at the entrance to the axial radial diffuser 5. From the annular space, air flow through the holes 8 in the walls of the flame tubes 4 enters
йнутрь этих труб, где участвует в процессегорени .The interior of these pipes, where it participates in the process of burning.
Фи9,2Fi9,2
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU843717918A SU1241805A1 (en) | 1984-04-02 | 1984-04-02 | Loop-type tubular-angular combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU843717918A SU1241805A1 (en) | 1984-04-02 | 1984-04-02 | Loop-type tubular-angular combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU1241805A1 true SU1241805A1 (en) | 1990-10-30 |
Family
ID=21110188
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SU843717918A SU1241805A1 (en) | 1984-04-02 | 1984-04-02 | Loop-type tubular-angular combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| SU (1) | SU1241805A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2717409C1 (en) * | 2018-11-30 | 2020-03-23 | Аслан Солтамбекович Тедтоев | Vertically oriented turbojet engine of power plant of vertical take-off and landing aircraft, vertical take-off and landing aircraft power plant, as well as vertical take-off and landing aircraft |
| RU2717606C1 (en) * | 2018-11-22 | 2020-03-24 | Аслан Солтамбекович Тедтоев | Aircraft vertical take-off and landing aircraft power plant, as well as vertical take-off and landing aircraft containing said power plant |
-
1984
- 1984-04-02 SU SU843717918A patent/SU1241805A1/en active
Non-Patent Citations (1)
| Title |
|---|
| П^^елкин Ю.М. Камеры сгорани газотурбинных двигателей. М.: Машиностроение, 1973, с.171, 1ЖС.9.7.Газотурбинные установки. Атлас конструкций и схем./ Под ред. Л.А.ЮубенкоНИубииа. М.: Машиностроение, 1976» с.126, рис.111-28. * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2717606C1 (en) * | 2018-11-22 | 2020-03-24 | Аслан Солтамбекович Тедтоев | Aircraft vertical take-off and landing aircraft power plant, as well as vertical take-off and landing aircraft containing said power plant |
| RU2717409C1 (en) * | 2018-11-30 | 2020-03-23 | Аслан Солтамбекович Тедтоев | Vertically oriented turbojet engine of power plant of vertical take-off and landing aircraft, vertical take-off and landing aircraft power plant, as well as vertical take-off and landing aircraft |
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