SU651218A2 - Probe for measuring parameters of three-dimensional flow - Google Patents
Probe for measuring parameters of three-dimensional flowInfo
- Publication number
- SU651218A2 SU651218A2 SU772535472A SU2535472A SU651218A2 SU 651218 A2 SU651218 A2 SU 651218A2 SU 772535472 A SU772535472 A SU 772535472A SU 2535472 A SU2535472 A SU 2535472A SU 651218 A2 SU651218 A2 SU 651218A2
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- tube
- probe
- dimensional flow
- measuring parameters
- pressure
- Prior art date
Links
Landscapes
- Measuring Temperature Or Quantity Of Heat (AREA)
Description
Изобретение относитс к области контрольно-измерительной техники, в частности к зондам д,л измерени статического и полного давлени в высокотемпературных потоках газа. По основному авт. св. № 303530 известно устройство, содержащее зонд дл измерени параметров пространственного потока с профилированным насадком обтекаемой формы, имеющий соединенные со вторичными приборами приемники давлени потока, расположенные в одной из взаимно перпендикул рных плоскостей, и приемники дл измерени давлени торможени и меридианального направлени потока, расположенные в другой плоскости под острыми углами один к другому, причем насадок выполнен в виде диска, а приемники дл измерени давлени торможени расположены по его кромке и выдвинуты за пределы диска. Однако отсутствует система охлаждени , что снижает надежность работы при высоких температурах газа. В предлагаемом зонде диск выполнен по контуру с канавкой под трубку дл хладагента и припа н к трубке, имеет державку, образованную параллельно расположенными концами трубки и припа нной между ними пневмотрассой статического давлени , а пневмотрассы давлени торможени размещены внутри трубки. На чертеже изображен предлагаемый зонд. Зонд содержит диск 1 с канавкой по контуру под трубку 2 дл хладагента. Трубка 2 припа на к диску. Концы трубки 2 расположены параллельно друг другу, а между ними размещена пневмотрасса 3 статического давлени . Концы трубки 2 и пневмотрасса 3 спа ны между собой и образуют державку диска 1. Пневмотрассы 4 давлени торможени раз.мещены внутри трубки 2. Трубка 2, а также пневмотрассы статического давлени и давлени торможени имеют штуцеры 5-8 соответственно. Испытани показывают, что максимально допусти.ма температура газового потока, при которой зонд работает надежно, составл ет 3000°К.The invention relates to the field of instrumentation technology, in particular, to probes for measuring the static and total pressure in high-temperature gas flows. According to the main author. St. No. 303530, a device comprising a probe for measuring spatial flow parameters with a shaped streamlined nozzle, having pressure flow receivers connected to secondary devices located in one of the mutually perpendicular planes, and receivers for measuring the stagnation pressure and meridional flow direction located in the other. angles to each other, the tips being made in the form of a disk, and the receivers for measuring the braking pressure are located along its edge and pushed out of the disc. However, there is no cooling system, which reduces the reliability of operation at high gas temperatures. In the proposed probe, the disk is made along a contour with a groove under the coolant tube and is poured to the tube, has a holder formed by parallel ends of the tube and the static pressure line fixed between them, and the braking pressure lines are located inside the tube. The drawing shows the proposed probe. The probe contains a disk 1 with a groove along the contour under the tube 2 for the refrigerant. Tube 2 solder to disk. The ends of the tube 2 are parallel to each other, and between them is placed the pneumatic rail 3 of static pressure. The ends of the tube 2 and the pneumatic track 3 are interconnected and form the holder of the disk 1. The pneumatic pressure tracks 4 of the braking pressure are placed inside the tube 2. The tube 2, as well as the pneumatics tracks of the static pressure and the braking pressure, have connections 5–8, respectively. Tests show that the maximum allowed gas flow temperature at which the probe works reliably is 3000 ° K.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU772535472A SU651218A2 (en) | 1977-10-21 | 1977-10-21 | Probe for measuring parameters of three-dimensional flow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU772535472A SU651218A2 (en) | 1977-10-21 | 1977-10-21 | Probe for measuring parameters of three-dimensional flow |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SU303530 Addition |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU651218A2 true SU651218A2 (en) | 1979-03-05 |
Family
ID=20729592
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SU772535472A SU651218A2 (en) | 1977-10-21 | 1977-10-21 | Probe for measuring parameters of three-dimensional flow |
Country Status (1)
| Country | Link |
|---|---|
| SU (1) | SU651218A2 (en) |
-
1977
- 1977-10-21 SU SU772535472A patent/SU651218A2/en active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4765751A (en) | Temperature and pressure probe | |
| Hottel et al. | Temperature measurements in high-velocity air streams | |
| SU651218A2 (en) | Probe for measuring parameters of three-dimensional flow | |
| CN106918437B (en) | Four-hole probe for measuring subsonic two-dimensional flow field | |
| SE7901124L (en) | CORROSION MONITORING DEVICE | |
| US3495915A (en) | Photoelectric probe detecting and measuring apparatus | |
| SU1530997A1 (en) | Primary transducer of device for measuring speed and direction of gas flow | |
| SU658400A1 (en) | Arrangement for checking rail lengthwise warping | |
| PIANKO | Modern methods of testing rotating components of turbomachines(instrumentation)(flow visualization, laser applications, and pressure sensors) | |
| US4198852A (en) | Inspection apparatus | |
| SU480980A1 (en) | Thermo-anemometer measuring probe | |
| NAKATANI et al. | Measurement of non-stationary flow by the pulse-laser induced luminescence method- Increase of observation rate | |
| SU1322114A1 (en) | Gripper for attaching specimens to testing machine in high-temperature strength testing | |
| US3273379A (en) | Method of locating leaks | |
| DUGGER | Optical instrumentation studies in aerospace facilities: A project summary(Optical measuring instruments used at hypervelocity ballistic range facility)[Final Report, Jul. 1971- Jun. 1972] | |
| FUNK | Optical probing of supersonic flows with statistical correlation(Optical sensing of supersonic flows by correlating deflections in laser beams through flow)[Patent] | |
| SU1138641A1 (en) | Linear displacement converter | |
| SU851228A2 (en) | Device for measuring enthalpy of high-temperature heterogenic gas flow | |
| SU1670380A1 (en) | Device for optically recording linear displacements of objects | |
| Dundr | Stagnation pressure and velocity measurement in high-temperature gases using pneumometric probes(Cooled miniature pneumometric probes for high temperature gases dynamic or stagnation pressure and velocity measurement) | |
| SU802878A2 (en) | Air flow direction meter | |
| AT349520B (en) | TRANSITIONAL PROTECTION BETWEEN TWO VEHICLES CONNECTED BY AN AUTOMATIC CENTRAL BUFFER COUPLING | |
| SU1060931A1 (en) | Instrument for measuring angle between article groove walls | |
| RO103374B1 (en) | Cooling device of samples with a view to impact elasticity testing at low temperatures | |
| Gahmousse | AN INVESTIGATION OF THE EFFECT OF PRESSURE GRADIENT, TEMPERATURE AND TEMPERATURE RATIO ON THE STAGNATION POINT HEAT TRANSFER. |