SU1468138A1 - Front device of gas-turbine engine combustion chamber - Google Patents
Front device of gas-turbine engine combustion chamber Download PDFInfo
- Publication number
- SU1468138A1 SU1468138A1 SU874241081A SU4241081A SU1468138A1 SU 1468138 A1 SU1468138 A1 SU 1468138A1 SU 874241081 A SU874241081 A SU 874241081A SU 4241081 A SU4241081 A SU 4241081A SU 1468138 A1 SU1468138 A1 SU 1468138A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- collector
- zone
- combustion chamber
- cavity
- ignition
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spark Plugs (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
Description
II
Изобретение относитс к турбо строению, в частности к фронтовым устройствам камер сгорани газотурбинных двигателей.The invention relates to a turbo structure, in particular to front-end devices of combustion chambers of gas turbine engines.
Целью изобретени вл етс повышение надежности воспламенени топ- лива.The aim of the invention is to improve the reliability of fuel ignition.
На фиг. 1 представлен продольный разрез фронтового устрой(гтва; на фиг. 2 - сечение А-А на фиг.1.FIG. 1 shows a longitudinal section of a front-end device (gtva; in Fig. 2, section A-A in Fig. 1.
Фронтовое устройство содержит ко- аксиально расположенные лопаточные завихрмтели 1 с противоположными углами за:крутки потока и размещен- ный между ними по меньшей мере один .The front device contains coaxially positioned blade swirlers 1 with opposite angles behind: the flow twists and at least one spaced between them.
коллектор 2 с отверсти ми 3, выпол- неннь т в его задней стенке 4,Устройство снабжено свечой 5 зажигани , а коллектор 2 - двум продольными пе-- регородками 6, образующими зональную полость 7, причем в перегородках 6 и в коллекторе 2 вьтолнены каналы 8 и 9 дл подвода в зональную полость 7 соответственно топлива и воздуха. Свеча 5 зажигани установлена на коллекторе 2 с выступанием ее электродов в упом нутую полость 7.the collector 2 with openings 3 is made in its rear wall 4, the device is equipped with a spark plug 5, and the collector 2 has two longitudinal partitions 6 forming a zone cavity 7, and the partitions are filled in partitions 6 and in the collector 2 8 and 9 for supplying fuel and air, respectively, to the zonal cavity 7. A spark plug 5 is mounted on a manifold 2 with its electrodes protruding into said cavity 7.
При работе камеры сгорани посту-, пивгоий в нее воздух проходит через завихрители 1 и образует за коллек00When the combustion chamber is in operation, the post-pivgoy air passes through it through the swirlers 1 and forms a collection
:о:about
тором циркул ционную зону, в которую через отверсти 3 в задней стенке i4 подводитс топливо. При этом часть топлива г пусковое топливо через каналы 8 в перегородках 6 попадает в запальную полость 7, где оно смешиваетс с воздухом, поступающим в эту полость 7 по каналам 9, и в виде топливсвоздушной смеси воспламен етс от свечи 5 зажигани . Гор ща смесь из полости 7 в виде запального факела через отверсти 3 в задней стенке f поступает в циркул ционную зону и воспламен ет подведенное в нее основное топлино.ттосле воспламенени основного топлива в циркул ционной зоне свеча 5 зажигани отключаетс .и горение в запальной полости 7 прекращаетс , а образующа в ней топливовоздушна смесь сгорает а задней стенкой А коллек- тора 2j воспламен сь при этом от факела основного топлива.The torus has a circulation zone into which fuel is supplied through the openings 3 in the rear wall of the i4. At the same time, part of the fuel and starting fuel through channels 8 in partitions 6 enters the firing cavity 7, where it is mixed with air entering this cavity 7 through channels 9, and in the form of an air-fuel mixture ignites from spark plug 5. The burning mixture from cavity 7 in the form of an ignition flame through openings 3 in the rear wall f enters the circulation zone and ignites the main fuel brought into it. After ignition of the main fuel in the circulation zone, the spark plug 5 is turned off. And the combustion in the ignition cavity 7 it stops, and the air-fuel mixture formed in it is burned, and the back wall A of the collector 2j is ignited from the main fuel plume.
ФормулаFormula
изобретени the invention
Фронтовое устройство камеры сгорани газотурбинного двигател , со-г держащее коаксиально расположенные .лопаточные завихрители с противоположными углами закрутки потока и размещенный между ними по меньшей мереThe front device of the combustion chamber of a gas turbine engine, which co-holds coaxially arranged blades with an opposite swirl angle and placed at least between them.
один коллектор с выполненными в его задней стенке отверсти ми, отличающеес тем, что, с целью повышени надежности воспламене1П1 топливаJ устройство- снабжено свечойOne collector with holes in its rear wall, characterized in that, in order to increase reliability, the 1P1 fuelJ device is equipped with a candle
зажигани , а коллектор - двум продольными перегородками, образующими запальную полость, причем в перегородках и в коллекторе вьтолнены каналы дл подвода в запальную полостьignition, and the collector - two longitudinal partitions that form the ignition cavity, and in the partitions and in the manifold channels for supplying the ignition cavity are filled
соответственно топлива и воздуха,fuel and air respectively
а свеча зажигани установлена на коллекторе с выступанием ее электродов в упом нутую полость.and a spark plug is installed on the manifold with the protrusion of its electrodes into the said cavity.
ИAND
ЩхShh
././
: :
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II
Составитель В.Жбаков.Compiled by V. Zhbakov.
Редактор А.Кондрахина Техред мГХоданич Корректор Л.ПилипенкоEditor A.Kondrakhina Tehred MGHodanich Proofreader L.Pilipenko
Заказ 3330Order 3330
Тираж 5Circulation 5
ВНШШИ Государственного комитета по изобретени м и открыти м при ГКНТ СССР 113035, Москва, Ж-35, Раушска наб., д. 4/5VNSHSHI of the State Committee for Inventions and Discoveries at the State Committee on Science and Technology of the USSR 4/5, Moscow, Zh-35, Raushsk nab. 113035
ПодписноеSubscription
Claims (1)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU874241081A SU1468138A1 (en) | 1987-05-05 | 1987-05-05 | Front device of gas-turbine engine combustion chamber |
DE19883814947 DE3814947A1 (en) | 1987-05-05 | 1988-05-03 | Combustion chamber for a turbine plant |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU874241081A SU1468138A1 (en) | 1987-05-05 | 1987-05-05 | Front device of gas-turbine engine combustion chamber |
Publications (1)
Publication Number | Publication Date |
---|---|
SU1468138A1 true SU1468138A1 (en) | 1990-09-23 |
Family
ID=21302718
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU874241081A SU1468138A1 (en) | 1987-05-05 | 1987-05-05 | Front device of gas-turbine engine combustion chamber |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE3814947A1 (en) |
SU (1) | SU1468138A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN113551260A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | V-shaped flame stabilizer with flow guide holes |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105781747B (en) * | 2016-03-22 | 2017-09-22 | 南京理工大学 | A kind of igniter for Liquid fuel ramjet engine |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SU642580A2 (en) * | 1977-08-24 | 1979-01-15 | Производственное Объединение "Невский Завод" Им. В.И.Ленина | Pilot flame igniter |
DE2740859C2 (en) * | 1977-09-10 | 1986-03-27 | Proizvodstvennoe ob"edinenie Nevskij zavod imeni V.I. Lenina, Leningrad | Annular combustion chamber |
-
1987
- 1987-05-05 SU SU874241081A patent/SU1468138A1/en active
-
1988
- 1988-05-03 DE DE19883814947 patent/DE3814947A1/en active Granted
Non-Patent Citations (1)
Title |
---|
Авторское свидетельство СССР 626314, кл. F 23 R 3/34, 1976. Авторское свидетельство СССР 493140, кл. F 23 R 3/16, 1974, .иепублик. * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN113551260A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | V-shaped flame stabilizer with flow guide holes |
Also Published As
Publication number | Publication date |
---|---|
DE3814947A1 (en) | 1988-11-24 |
DE3814947C2 (en) | 1991-01-31 |
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