GB796027A - Improvements in jet propulsion nozzles - Google Patents
Improvements in jet propulsion nozzlesInfo
- Publication number
- GB796027A GB796027A GB11994/56A GB1199456A GB796027A GB 796027 A GB796027 A GB 796027A GB 11994/56 A GB11994/56 A GB 11994/56A GB 1199456 A GB1199456 A GB 1199456A GB 796027 A GB796027 A GB 796027A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzle
- jet
- manifold
- pipes
- jet propulsion
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
- F02K1/30—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for varying effective area of jet pipe or nozzle
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Investigating, Analyzing Materials By Fluorescence Or Luminescence (AREA)
- Testing Of Engines (AREA)
Abstract
796,027. Generating combustion products under pressure. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. April 19, 1956 [April 22, 1955], No. 11994/56. Addition to 750,616, [Group XXVI) Class 51 (1). [Also in Group XXVI] A variable area jet propulsion nozzle as claimed in the parent Specification in which the jet formed by the nozzle is controlled by an auxiliary fluid injected into the main stream in a direction substantially perpendicular to, or inclined upstream to, the direction of the main flow and in which the momentum of the auxiliary fluid is increased by heating by internal combustion, has the means for heating the auxiliary fluid arranged in an annular manifold extending around the propulsion nozzle. The rear portion, Fig. 1, of a jet propulsion nozzle has an annular manifold 2 arranged around its outlet end which receives air from the compressor of the jet propulsion engine or any other source of suitable pressure through one or more piping systems 3. The manifold 2 discharges through a nozzle 4, in the form of a slot, into the main jet flow F so as to form an aerodynamic screen which reduces the outlet cross-section of the nozzle. A flame tube 5 with fuel injectors 6 is located in the manifold 2. Primary air from the pipes 3 passes into the tube 5 through holes 7. The remainder passes between the tube 5 and the wall of the manifold 2 where it is divided. Part of this air flow through the holes 8 to act as secondary air and the remainder is mixed with the combustion gases leaving the flame tube 5 through the slot 9. Igniters 10 are provided adjacent one or more of the injectors 6. The effective area of the nozzle may be varied by varying the flow in the pipes 3 and to the fuel injectors 6. The nozzle is specially suitable for use with a gas turbine jet propulsion engine having reheat in the jet pipe. In a modification, the partitions 11 in the flame tube 5, between the fuel injectors 6 are dispensed with and the pipes 3 are replaced by two groups of pipes arranged on diametrically opposite sides of the propulsion nozzle. The nozzle is cooled by an air stream F3 which passes through channels 14 formed in the opposite walls of the nozzle 4. Specification 745,630 and 759,659, [both in Group XXVI], are referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR796027X | 1955-04-22 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB796027A true GB796027A (en) | 1958-06-04 |
Family
ID=9234920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB11994/56A Expired GB796027A (en) | 1955-04-22 | 1956-04-19 | Improvements in jet propulsion nozzles |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB796027A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1918561A3 (en) * | 2006-10-24 | 2011-03-30 | United Technologies Corporation | Combustion nozzle fluidic injection assembly |
| RU2536460C2 (en) * | 2012-07-12 | 2014-12-27 | Валерий Григорьевич Кехваянц | Thrust generation in jet engine and jet nozzle to this end |
-
1956
- 1956-04-19 GB GB11994/56A patent/GB796027A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1918561A3 (en) * | 2006-10-24 | 2011-03-30 | United Technologies Corporation | Combustion nozzle fluidic injection assembly |
| RU2536460C2 (en) * | 2012-07-12 | 2014-12-27 | Валерий Григорьевич Кехваянц | Thrust generation in jet engine and jet nozzle to this end |
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