SU956832A1 - Unit for determining gas medium velocity in fuel torch - Google Patents
Unit for determining gas medium velocity in fuel torch Download PDFInfo
- Publication number
- SU956832A1 SU956832A1 SU813254878A SU3254878A SU956832A1 SU 956832 A1 SU956832 A1 SU 956832A1 SU 813254878 A SU813254878 A SU 813254878A SU 3254878 A SU3254878 A SU 3254878A SU 956832 A1 SU956832 A1 SU 956832A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- fuel
- chambers
- gas medium
- nozzle
- velocity
- Prior art date
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- Measuring Fluid Pressure (AREA)
Description
(54) УСТАНОВКА ДЛЯ ОПРЕДЕЛЕНИЯ СКОРОСТИ ДВИЖЕНИЯ ГАЗОВОЙ СРЕДЫ В ТОПЛИВНОМ ФАКЕЛЕ(54) INSTALLATION TO DETERMINE THE VELOCITY OF THE GAS ENVIRONMENT IN A FUEL TORCH
1one
Изобретение относитс к исследованию топливной аппаратуры двигателей внутреннего сгорани и предназначено дл исследовани структуры топливного факела.The invention relates to the investigation of the fuel apparatus of internal combustion engines and is intended to investigate the structure of the fuel plume.
Известна установка дл определени скорости движени в топливном факеле, содержаща герметичный корпус с внутренней полостью, разделенной на две камеры перегородкой с осевым отверстием, расположенным соосно с сопловым отверстием распылител форсунки, причем перегородка установлена в корпусе с возможностью осевого перемещени и фиксации, а форсунка соединена с гидроаккумул тором, подключенным к топливному насосу высокого давлени , и систему создани и измерени давлени газовой среды и слива топлива из камер 1.A known installation for determining the speed of movement in a fuel plume, comprising a sealed housing with an internal cavity divided into two chambers with an axial bore disposed coaxially with the nozzle orifice of the atomizer nozzle, the partition mounted in the housing with the possibility of axial displacement and fixation, and the nozzle is connected to a hydroaccumulator connected to the high-pressure fuel pump, and a system for creating and measuring the pressure of the gaseous medium and the discharge of fuel from the chambers 1.
Недостаток установки состоит в том, что вследствие эжектировани газа топливным факелом при прохождении отверсти в перегородке , давление за перегородкой возрастает , а это вызывает торможение потока эжектируемого газа и заметное искажение структуры топливного факела ло сравнению с действительной в камере сгорани двигател . Известна установка не позвол етThe disadvantage of the installation is that due to gas ejection by the fuel torch when the hole in the partition passes, the pressure behind the partition increases, and this causes braking of the flow of the ejected gas and a noticeable distortion of the structure of the fuel plume compared with the actual in the engine combustion chamber. Known installation does not allow
определить скорость движени газовой среды без внесени значительных погрешностей. Целью изобретени вл етс повышение точности определени скорости движени газовой среды путем уменьщёни перепадаdetermine the velocity of the gas medium without introducing significant errors. The aim of the invention is to improve the accuracy of determining the velocity of the gas environment by reducing the differential
давлени между камерами. pressure between chambers.
Поставленна цель достигаетс тем, что камеры сообщены между собой при помощи трубопровода, снабженного устройством дл замера расхода газа.This goal is achieved by the fact that the chambers communicate with each other by means of a pipeline equipped with a device for measuring gas flow.
10 На чертеже приведена конструктивна схема предлагаемой установки.10 The drawing shows a constructive scheme of the proposed installation.
В герметичный корпус 1 установлена перегородка 2, раздел юща . внутреннюю полость корпуса на две камеры, регулируемые по объему перемещением и фиксацией штока 3. В перегородке 2 выполнено осевое отверстие, соосно которому расположено сопловое отверстие распылител форсунки 4, установленной в корпусе 1 напротив перегородки 2.A septum 2 is installed in the hermetic case 1, which separates it. the internal cavity of the body into two chambers, regulated in volume by movement and fixation of the rod 3. In the partition 2 there is an axial hole coaxially with which there is a nozzle hole of the spray nozzle 4 installed in the housing 1 opposite the partition 2.
20 Установка содержит систему 5 слива топлива и систему 6 наполнени газом с манометром 7. Форсунка 4 подключена к гидравлическому аккумул тору 8, к которому топливо подводитс от насоса высокого дав20 The installation contains a fuel discharge system 5 and a gas filling system 6 with a pressure gauge 7. The nozzle 4 is connected to a hydraulic accumulator 8 to which fuel is supplied from a high pressure pump
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU813254878A SU956832A1 (en) | 1981-02-23 | 1981-02-23 | Unit for determining gas medium velocity in fuel torch |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU813254878A SU956832A1 (en) | 1981-02-23 | 1981-02-23 | Unit for determining gas medium velocity in fuel torch |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU956832A1 true SU956832A1 (en) | 1982-09-07 |
Family
ID=20945570
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SU813254878A SU956832A1 (en) | 1981-02-23 | 1981-02-23 | Unit for determining gas medium velocity in fuel torch |
Country Status (1)
| Country | Link |
|---|---|
| SU (1) | SU956832A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5412981A (en) * | 1993-09-07 | 1995-05-09 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Apparatus for testing high pressure injector elements |
-
1981
- 1981-02-23 SU SU813254878A patent/SU956832A1/en active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5412981A (en) * | 1993-09-07 | 1995-05-09 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Apparatus for testing high pressure injector elements |
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