GB1105955A - Improvements in or relating to ejectors used for engine simulation - Google Patents
Improvements in or relating to ejectors used for engine simulationInfo
- Publication number
- GB1105955A GB1105955A GB3844764A GB3844764A GB1105955A GB 1105955 A GB1105955 A GB 1105955A GB 3844764 A GB3844764 A GB 3844764A GB 3844764 A GB3844764 A GB 3844764A GB 1105955 A GB1105955 A GB 1105955A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- duct
- vanes
- nozzles
- passage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Abstract
1,105,955. Wind tunnels. BRITISH AIR. CRAFT CORPORATION (OPERATING) Ltd. 21 Sept., 1965 [21 Sept., 1964], No. 38447/64. Heading B7G. [Also in Division F1] An ejector comprises a duct formed between a central body 14 and a casing 10, downstreamfacing nozzles 19 distributed across the duct and supplied with air from branched passages 20, 13, 17, 18, each branch having such an airflow resistance that air is discharged from the nozzles to provide a substantially uniform mass flow rate across the whole section of the duct. The ejector is used for simultating the air flow pattern around the intake or exhaust of an airbreathing engine. An annular baffle 22 may be arranged in cavity 13 to equalize the flow rates between each set of vanes 17 and 18. In another embodiment only one set of vanes is present, air being supplied to both ends of the vanes which are each divided into two passages by a lengthwise wall. Both passages communicate with the air supply at their outer ends. One passage has the nozzles and a restriction at its outer end whilst the other passage constitutes a duct supplying air to the inner end of the first passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3844764A GB1105955A (en) | 1964-09-21 | 1964-09-21 | Improvements in or relating to ejectors used for engine simulation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3844764A GB1105955A (en) | 1964-09-21 | 1964-09-21 | Improvements in or relating to ejectors used for engine simulation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1105955A true GB1105955A (en) | 1968-03-13 |
Family
ID=10403507
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3844764A Expired GB1105955A (en) | 1964-09-21 | 1964-09-21 | Improvements in or relating to ejectors used for engine simulation |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1105955A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50152110A (en) * | 1974-05-28 | 1975-12-06 | ||
| CN114018542A (en) * | 2021-11-02 | 2022-02-08 | 中国航发沈阳发动机研究所 | Testing device applying magnetohydrodynamic technology in engine flow channel |
| CN115436009A (en) * | 2022-11-08 | 2022-12-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Nozzle thrust measurement test system with integrated rear body and nozzle |
-
1964
- 1964-09-21 GB GB3844764A patent/GB1105955A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50152110A (en) * | 1974-05-28 | 1975-12-06 | ||
| CN114018542A (en) * | 2021-11-02 | 2022-02-08 | 中国航发沈阳发动机研究所 | Testing device applying magnetohydrodynamic technology in engine flow channel |
| CN115436009A (en) * | 2022-11-08 | 2022-12-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Nozzle thrust measurement test system with integrated rear body and nozzle |
| CN115436009B (en) * | 2022-11-08 | 2023-01-31 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet pipe thrust measurement test system with integrally designed afterbody and jet pipe |
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