GB506699A - Improvements in and relating to the utilisation of the exhaust gas energy of aircraft engines for propulsion purposes - Google Patents
Improvements in and relating to the utilisation of the exhaust gas energy of aircraft engines for propulsion purposesInfo
- Publication number
- GB506699A GB506699A GB19556/38A GB1955638A GB506699A GB 506699 A GB506699 A GB 506699A GB 19556/38 A GB19556/38 A GB 19556/38A GB 1955638 A GB1955638 A GB 1955638A GB 506699 A GB506699 A GB 506699A
- Authority
- GB
- United Kingdom
- Prior art keywords
- exhaust
- critical
- nozzle
- exhaust pipe
- pressure
- 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
- 239000007789 gas Substances 0.000 abstract 2
- 230000001141 propulsive effect Effects 0.000 abstract 1
- 238000010992 reflux Methods 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust Silencers (AREA)
Abstract
506,699. Exhaust systems. JUNKERS FLUGZEUG - <SB>UND <SB>MOTORENWERKE AKT.-GES. July 1,1938, No. 19556. Convention date, July 1, 1937. [Class 7 (ii)] [Also in Group XXXIII] The exhaust gases from each cylinder of an aero-engine are discharged into separate pipes each having at its end a nozzle whereby the outlet velocity of the exhaust gas and consequently the reflux propulsive force or impulse is in. creased. When the pressure outside the exhaust pipe during the greater period of the exhaust discharge is greater than the critical pressure, determined by the pressure and velocityin the pipe the nozzle tapers to minimum cross section at the outlet, the taper ratio lying between 0À3 and I. Further the cubic capacity of the exhaust pipe may be between 0À3 and 1 of the swept volume of the working cylinder. When the velocity of flow in the exhaust pipe is super-critical and the external pressure is generally below the critical the nozzle' is given a. convergent-divergent form. If the velocity of flow in the exhaust pipe during a considerable period of the discharge is super-critical the nozzle is given a divergent form. In one constructional form the exhaust, pipes 32f ... 33f ... are arranged as shown in Fig. 8 and in another form, they are surrounded by a cowling 40 having inlet and outlet apertures 42, 41.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE506699X | 1950-10-31 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB506699A true GB506699A (en) | 1939-06-02 |
Family
ID=6546626
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB19556/38A Expired GB506699A (en) | 1937-07-01 | 1938-07-01 | Improvements in and relating to the utilisation of the exhaust gas energy of aircraft engines for propulsion purposes |
Country Status (3)
| Country | Link |
|---|---|
| BE (1) | BE506699A (en) |
| ES (1) | ES145814A1 (en) |
| GB (1) | GB506699A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE749103C (en) * | 1940-03-14 | 1944-11-15 | Flame suppressor with recoil effect | |
| DE749457C (en) * | 1940-12-11 | 1944-11-23 | Device for utilizing the recoil of exhaust gases from internal combustion engines for flame dampening and heating in aircraft | |
| DE848725C (en) * | 1942-12-20 | 1952-09-08 | Daimler Benz Ag | Device for the improved utilization of the energy of the exhaust gases from exhaust aircraft engines by generating recoil with simultaneous flame absorption |
-
1938
- 1938-06-30 ES ES0145814A patent/ES145814A1/en not_active Expired
- 1938-07-01 GB GB19556/38A patent/GB506699A/en not_active Expired
-
1951
- 1951-10-26 BE BE506699A patent/BE506699A/en unknown
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE749103C (en) * | 1940-03-14 | 1944-11-15 | Flame suppressor with recoil effect | |
| DE749457C (en) * | 1940-12-11 | 1944-11-23 | Device for utilizing the recoil of exhaust gases from internal combustion engines for flame dampening and heating in aircraft | |
| DE848725C (en) * | 1942-12-20 | 1952-09-08 | Daimler Benz Ag | Device for the improved utilization of the energy of the exhaust gases from exhaust aircraft engines by generating recoil with simultaneous flame absorption |
Also Published As
| Publication number | Publication date |
|---|---|
| ES145814A1 (en) | 1940-09-01 |
| BE506699A (en) | 1953-03-13 |
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