SU200964A1 - FIRE CHARGE FOR COMBUSTION CHAMBERS - Google Patents
FIRE CHARGE FOR COMBUSTION CHAMBERSInfo
- Publication number
- SU200964A1 SU200964A1 SU1060581A SU1060581A SU200964A1 SU 200964 A1 SU200964 A1 SU 200964A1 SU 1060581 A SU1060581 A SU 1060581A SU 1060581 A SU1060581 A SU 1060581A SU 200964 A1 SU200964 A1 SU 200964A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- combustion chambers
- cylinder
- holes
- fire charge
- cone
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 title description 5
- 235000010599 Verbascum thapsus Nutrition 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
Description
Известны пламенные трубы дл камер сгорани газотурбинных установок, состо щие из двух перфорированных соосных цилиндров.Flame pipes are known for combustion chambers of gas-turbine installations consisting of two perforated coaxial cylinders.
В предлагаемой трубе наружный цилиндр выполнен гофрированным дл интенсификации процесса сгорани и уменьшени длины камеры .In the proposed pipe, the outer cylinder is made corrugated to intensify the combustion process and reduce the length of the chamber.
На фиг. 1 дана схема предлагаемой трубы; iia фиг. 2 - узел Л в увеличенном масштабе.FIG. 1 is a diagram of the proposed pipe; iia FIG. 2 - node L on an enlarged scale.
Пламенна труба состоит из внутреннего гладкостенного цилиндра /, соосно с которым расположен гофрированный цилиндр 2, вплотную примыкающий к внутреннему вершинами гофр. В головной части трубы расположен гофрированный конус 3.The flame tube consists of an internal smooth-walled cylinder /, coaxial with which is a corrugated cylinder 2, the corrugation adjacent to the inner apex. A corrugated cone 3 is located at the head of the pipe.
На поверхности внутреннего цилиндра и на конусе высверлено много отверстий малого диаметра. На вершинах гофр, не примыкающих к поверхности цилиндра и конуса, высверлены отверсти такого же диаметра, но сдвинутые на полшага вдоль образующей цилиндра или конуса. Диаметр и количество отверстий выбираетс так, чтобы скорость воздуха в отверсти х составл ла 40-50 м/сек, а шаг и высота гофра - так, чтобы скорость Many small-diameter holes are drilled on the surface of the inner cylinder and on the cone. On the tops of the corrugations that are not adjacent to the surface of the cylinder and the cone, holes of the same diameter are drilled, but shifted half a step along the generator of the cylinder or cone. The diameter and number of holes is chosen so that the air velocity in the holes is 40-50 m / s, and the pitch and height of the corrugation is chosen so that the speed
воздуха в каналах между внутренним цилиндром и наружным составл ла 15--25 м/сек.The air in the channels between the inner cylinder and the outer cylinder was 15-25 m / s.
Металл внутреннего цилиндра охлаждаетс вследствие лобового удара струй воздуха, вытекающих с большой скоростью из отверстий в гофрах, а также вследствие конвективного теплосъема в пространстве между наружным и внутренним цилиндрами. Воздух, вытекаюН1 ,ий из отверстий внутреннего цилиндра и конуса, создает заградительную воздушную пленку со стороны факела.The metal of the inner cylinder is cooled due to a frontal impact of air jets flowing at high speed from the holes in the corrugations, as well as due to convective heat removal in the space between the outer and inner cylinders. The air flowing out of the holes of the inner cylinder and the cone creates a barrier air film from the side of the torch.
Компенсаци тепловых расширений при неодинаковом нагреве внутреннего и наружного цилиндров осуществл етс путем некоторого раст жени гофрировки по окружности.Compensation of thermal expansions for unequal heating of the inner and outer cylinders is accomplished by some extension of the corrugation around the circumference.
Предмет изобретени Subject invention
Пламенна труба дл камер сгорани газо урбинных установок, состо ща из двух перфорированных соосных цилиндров, OT.iU4.aioща с тем, что, с целью интенсификации процесса сгорани и уменьшени длины камеры, наружный цилиндр выполнен гофрированным.The flame tube for the combustion chambers of gas from urban installations, consisting of two perforated coaxial cylinders, OT.iU4.a, with the aim of intensifying the outer cylinder to increase the combustion process and reduce the chamber length.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU200964A1 true SU200964A1 (en) |
Family
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4109459A (en) * | 1974-07-19 | 1978-08-29 | General Electric Company | Double walled impingement cooled combustor |
| US4174608A (en) * | 1972-08-15 | 1979-11-20 | Stal-Laval Turbin Ab | Combustion chamber for a gas turbine |
| US4236378A (en) * | 1978-03-01 | 1980-12-02 | General Electric Company | Sectoral combustor for burning low-BTU fuel gas |
| US4422300A (en) * | 1981-12-14 | 1983-12-27 | United Technologies Corporation | Prestressed combustor liner for gas turbine engine |
| US4607487A (en) * | 1981-12-31 | 1986-08-26 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Combustion chamber wall cooling |
| US4695247A (en) * | 1985-04-05 | 1987-09-22 | Director-General Of The Agency Of Industrial Science & Technology | Combustor of gas turbine |
| US4872312A (en) * | 1986-03-20 | 1989-10-10 | Hitachi, Ltd. | Gas turbine combustion apparatus |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4174608A (en) * | 1972-08-15 | 1979-11-20 | Stal-Laval Turbin Ab | Combustion chamber for a gas turbine |
| US4109459A (en) * | 1974-07-19 | 1978-08-29 | General Electric Company | Double walled impingement cooled combustor |
| US4236378A (en) * | 1978-03-01 | 1980-12-02 | General Electric Company | Sectoral combustor for burning low-BTU fuel gas |
| US4422300A (en) * | 1981-12-14 | 1983-12-27 | United Technologies Corporation | Prestressed combustor liner for gas turbine engine |
| US4607487A (en) * | 1981-12-31 | 1986-08-26 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Combustion chamber wall cooling |
| US4695247A (en) * | 1985-04-05 | 1987-09-22 | Director-General Of The Agency Of Industrial Science & Technology | Combustor of gas turbine |
| US4872312A (en) * | 1986-03-20 | 1989-10-10 | Hitachi, Ltd. | Gas turbine combustion apparatus |
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