SU720252A1 - Burner for combustion chamber - Google Patents
Burner for combustion chamber Download PDFInfo
- Publication number
- SU720252A1 SU720252A1 SU782650042A SU2650042A SU720252A1 SU 720252 A1 SU720252 A1 SU 720252A1 SU 782650042 A SU782650042 A SU 782650042A SU 2650042 A SU2650042 A SU 2650042A SU 720252 A1 SU720252 A1 SU 720252A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- burner
- inlet
- combustion chamber
- outlet
- casing
- Prior art date
Links
Landscapes
- Spray-Type Burners (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Description
II
Изобретение относитс к воздушнореактивным двигател м, в частности к горелкам камер сгорани .This invention relates to air-jet engines, in particular to burners of combustion chambers.
Известна горелка камеры, сгорани , содержаща испаритель, выполненный в виде трубки Т-образной формы, имеющей топливную форсунку, установленную на аходе, и отражатель - на . выходе 1.A known burner chamber, a combustion containing an evaporator made in the form of a T-shaped tube having a fuel nozzle installed at the entrance, and a reflector. output 1.
Однако в известной горелке, вследствие неудовлетворительного смесеобразовани топлива с воздухом, ухудшаютс технико-экономические характеристики.However, in a known burner, due to the poor mixture of fuel with air, the technical and economic characteristics are deteriorated.
Известна также горе ка камеры сгорани содержаща кольцевую обечайку с наружным завихрителем на выходе, и соосно расположенные в ней на вхсде топливную форсунку и зави.хритель 2.The mount of the combustion chamber is also known, which contains an annular shell with an outer swirler at the outlet, and a fuel injector coaxially located in it on the inside of the valve and the dependence 2.
Однако известна горелка имеет недостаточно широкий диапазон устойчивой работы.However, the known burner has an insufficiently wide range of stable operation.
Целью изобретени вл етс расигаре- ние диапазона устойчивой работы и улучшение смесеобразовани .The aim of the invention is to decipher the range of stable operation and improve the mixture formation.
Указанна цепь достигаетс тем, что в обечайке выполнены продольные сквозные каналы с установленными на входе топливными форсунками, а на выходе обечайки .установлен радиальный дефлектор .This chain is achieved by the fact that the shell has longitudinal through channels with fuel injectors installed at the inlet and a radial deflector installed at the shell outlet.
На фиг. 1 представлен продольный резрез горелки на фиг. 2 - разрез А-А фиг. 1.FIG. 1 shows the longitudinal cut of the burner in FIG. 2 - section A-A of FIG. one.
Горелка камеры сгорани содержит кольцевую обечайку 1 с наружным завихрителем 2 на входе. Соосно обечайке 1 на входе в нее расположены-топливна форсунка 3 и завихритель 4. Обечайка 1 имеет продольные сквозные каналы 5 с установленными на входе топлив 1ыми форсунками 6, а на выходе из обечайки установлен радиальный дефлекторThe burner of the combustion chamber contains an annular shell 1 with an outer swirler 2 at the inlet. The fuel injector 3 and the swirler 4 are located coaxially to the shell 1 at the entrance to it. Shell 1 has longitudinal through channels 5 with 1st injectors 6 installed at the fuel inlet, and a radial deflector is installed at the outlet of the shell
7.7
Горелка установлена на входе в жаровую трубу 8.The burner is installed at the entrance to the flame tube 8.
При работе горелки часть первичного воздуха поступает через завкхритель 2 в жаровую трубу 8, где образуетс необDuring the operation of the burner, a part of the primary air enters through the control unit 2 into the flame tube 8, where it is formed
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU782650042A SU720252A1 (en) | 1978-07-17 | 1978-07-17 | Burner for combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU782650042A SU720252A1 (en) | 1978-07-17 | 1978-07-17 | Burner for combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU720252A1 true SU720252A1 (en) | 1980-03-05 |
Family
ID=20779414
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SU782650042A SU720252A1 (en) | 1978-07-17 | 1978-07-17 | Burner for combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| SU (1) | SU720252A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4362021A (en) * | 1979-08-01 | 1982-12-07 | Rolls-Royce Limited | Gas turbine engine fuel injectors |
| US5165241A (en) * | 1991-02-22 | 1992-11-24 | General Electric Company | Air fuel mixer for gas turbine combustor |
| US5251447A (en) * | 1992-10-01 | 1993-10-12 | General Electric Company | Air fuel mixer for gas turbine combustor |
-
1978
- 1978-07-17 SU SU782650042A patent/SU720252A1/en active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4362021A (en) * | 1979-08-01 | 1982-12-07 | Rolls-Royce Limited | Gas turbine engine fuel injectors |
| US5165241A (en) * | 1991-02-22 | 1992-11-24 | General Electric Company | Air fuel mixer for gas turbine combustor |
| US5251447A (en) * | 1992-10-01 | 1993-10-12 | General Electric Company | Air fuel mixer for gas turbine combustor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US3643430A (en) | Smoke reduction combustion chamber | |
| US4194358A (en) | Double annular combustor configuration | |
| US4356698A (en) | Staged combustor having aerodynamically separated combustion zones | |
| GB2242734A (en) | Lean staged combustion assembly | |
| GB1427146A (en) | Combustion apparatus for gas turbine engines | |
| CA1136434A (en) | Lean prechamber outflow combustor with continuous pilot flow | |
| US4365477A (en) | Combustion apparatus for gas turbine engines | |
| KR100679596B1 (en) | Radial inflow dual fuel injector | |
| SU720252A1 (en) | Burner for combustion chamber | |
| JPS5546309A (en) | Burner for gas turbine | |
| US3267676A (en) | Fuel burner structure | |
| US4170109A (en) | Thrust augmentor having swirled flows for combustion stabilization | |
| USRE30160E (en) | Smoke reduction combustion chamber | |
| RU2098719C1 (en) | Power plant gas turbine combustion chamber | |
| GB2013788A (en) | Gas turbine engine combustion equipment | |
| US5115637A (en) | External cartridge gas combustor ignitor | |
| SU1726917A1 (en) | Annular combustion chamber of gas-turbine engine | |
| GB757871A (en) | Improvements in and relating to combustion chambers | |
| GB1450649A (en) | Premix combustion assembly | |
| SU981759A1 (en) | Gas mazut burner | |
| SU1195135A1 (en) | Burner for burning liquid fuel | |
| RU527933C (en) | Burner for combustion chamber of gas-turbine engine | |
| SU1195137A1 (en) | Oil-gas burner | |
| SU393539A1 (en) | EVAPORATIVE COMBUSTION CHAMBER OF A GAS TURBINE | |
| SU1002736A2 (en) | Combustion chamber |