RU2009116298A - COMBUSTION CAMERA OF A GAS TURBINE ENGINE - Google Patents
COMBUSTION CAMERA OF A GAS TURBINE ENGINE Download PDFInfo
- Publication number
- RU2009116298A RU2009116298A RU2009116298/06A RU2009116298A RU2009116298A RU 2009116298 A RU2009116298 A RU 2009116298A RU 2009116298/06 A RU2009116298/06 A RU 2009116298/06A RU 2009116298 A RU2009116298 A RU 2009116298A RU 2009116298 A RU2009116298 A RU 2009116298A
- Authority
- RU
- Russia
- Prior art keywords
- combustion chamber
- nozzles
- cavity
- flame tube
- air
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract 21
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title 1
- 239000000446 fuel Substances 0.000 claims abstract 4
- 241000237858 Gastropoda Species 0.000 claims abstract 2
- 239000007788 liquid Substances 0.000 claims abstract 2
Abstract
1. Камера сгорания газотурбинного двигателя, содержащая корпус, в котором установлена жаровая труба с отверстиями для пропускания воздуха и с завихрителем на входе, форсунка для подачи топлива в зону горения, отличающаяся тем, что в корпусе камеры сгорания соосно первой установлена вторая жаровая труба, на входе в которую установлен двухрядный завихритель, причем камера сгорания оснащена насадками и форсунками для подачи жидкого или газообразного топлива в полость второй жаровой трубы, а во второй жаровой трубе выполнены отверстия для пропускания воздуха в ее полость, при этом камера сгорания снабжена газосборником, размещенном в корпусе, состыкованном с корпусом камеры сгорания, полости камеры сгорания и корпуса газосборника изолированы друг от друга, корпус газосборника оснащен патрубками для прохода через полость воздуха, подаваемого из-за компрессора в теплообменник, а камера сгорания - патрубками для подвода воздуха от теплообменника в полость камеры сгорания. ! 2. Камера сгорания газотурбинного двигателя по п.1, отличающаяся тем, что газосборник имеет тороидальную улиточную форму. 1. The combustion chamber of a gas turbine engine, comprising a housing in which a flame tube is installed with openings for air passage and with a swirl inlet, an injector for supplying fuel to the combustion zone, characterized in that the second flame tube is coaxially installed in the combustion chamber body first, the entrance to which a double-row swirler is installed, and the combustion chamber is equipped with nozzles and nozzles for supplying liquid or gaseous fuel to the cavity of the second flame tube, and openings are made in the second flame tube lowering air into its cavity, while the combustion chamber is equipped with a gas collector located in a housing docked with the housing of the combustion chamber, the cavities of the combustion chamber and the body of the gas collector are isolated from each other, the gas collector body is equipped with nozzles for passage through the air cavity supplied by the compressor to a heat exchanger, and the combustion chamber - with nozzles for supplying air from the heat exchanger to the cavity of the combustion chamber. ! 2. The combustion chamber of a gas turbine engine according to claim 1, characterized in that the gas collector has a toroidal snail shape.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2009116298/06A RU2414649C2 (en) | 2009-04-30 | 2009-04-30 | Gas turbine engine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2009116298/06A RU2414649C2 (en) | 2009-04-30 | 2009-04-30 | Gas turbine engine combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2009116298A true RU2009116298A (en) | 2010-11-10 |
| RU2414649C2 RU2414649C2 (en) | 2011-03-20 |
Family
ID=44025650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2009116298/06A RU2414649C2 (en) | 2009-04-30 | 2009-04-30 | Gas turbine engine combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2414649C2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8820090B2 (en) * | 2012-09-05 | 2014-09-02 | Siemens Aktiengesellschaft | Method for operating a gas turbine engine including a combustor shell air recirculation system |
| RU2626892C2 (en) * | 2015-11-06 | 2017-08-02 | федеральное государственное автономное образовательное учреждение высшего образования "Южно-Уральский государственный университет (национальный исследовательский университет)" | Gas-turbine engine direct-flow combustion chamber |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2098720B (en) * | 1979-01-12 | 1983-04-27 | Gen Electric | Stationary gas turbine combustor arrangements |
| DE2937631A1 (en) * | 1979-09-18 | 1981-04-02 | Daimler-Benz Ag, 7000 Stuttgart | COMBUSTION CHAMBER FOR GAS TURBINES |
| FR2673455A1 (en) * | 1991-02-28 | 1992-09-04 | Snecma | LOW PRE-COMBUSTION COMBUSTION CHAMBER HAVING A COUNTER-CURRENT SPEAKER FOR STABILIZING THE FLAME OF THE PREMIX. |
| RU64324U1 (en) * | 2007-03-05 | 2007-06-27 | Открытое акционерное общество "Самарское конструкторское бюро машиностроения" | COMBUSTION CAMERA OF A GAS TURBINE ENGINE |
-
2009
- 2009-04-30 RU RU2009116298/06A patent/RU2414649C2/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| RU2414649C2 (en) | 2011-03-20 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20110501 |