DE2311456A1 - PUMPING DEVICE FOR AIRPLANE FUEL TANKS - Google Patents
PUMPING DEVICE FOR AIRPLANE FUEL TANKSInfo
- Publication number
- DE2311456A1 DE2311456A1 DE19732311456 DE2311456A DE2311456A1 DE 2311456 A1 DE2311456 A1 DE 2311456A1 DE 19732311456 DE19732311456 DE 19732311456 DE 2311456 A DE2311456 A DE 2311456A DE 2311456 A1 DE2311456 A1 DE 2311456A1
- Authority
- DE
- Germany
- Prior art keywords
- pump
- pumping device
- fuel
- fuel tanks
- fuel tank
- 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.)
- Pending
Links
- 239000002828 fuel tank Substances 0.000 title claims description 11
- 238000005086 pumping Methods 0.000 title description 5
- 239000000446 fuel Substances 0.000 claims description 9
- 239000007788 liquid Substances 0.000 claims description 4
- 238000000605 extraction Methods 0.000 claims 1
- 230000006698 induction Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M37/00—Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
- F02M37/20—Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines characterised by means for preventing vapour lock
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/14—Filling or emptying
- B64D37/16—Filling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
PATENTANWÄLTE
Dip!.-Ing.WERNER COHAUSZ · Dipl.-Ing. WILHELM FLORACK. Dipl-Ing. RUDOLF KNAUFPATENT LAWYERS
Dip! .- Ing.WERNER COHAUSZ · Dipl.-Ing. WILHELM FLORACK. Dipl-Ing. RUDOLF KNAUF
4 Düsseldorf, Schumannstraße 974 Düsseldorf, Schumannstrasse 97
7. März. 19757th March. 1975
Lucas Aerospace Ltd.Lucas Aerospace Ltd.
Well Street
GB-BirminghamWell Street
GB-Birmingham
Die vorliegende Erfindung bezieht sich auf Pumpvorrichtungen für den Einsatz in Flugzeug-Kraftstofftanks. Der Erfindung liegt die Aufgabe zugrunde, eine derartige Vorrichtung in einer zweckmäßigen Ausführungsform zu schaffen.The present invention relates to pumping devices for use in aircraft fuel tanks. The invention The object of the invention is to provide such a device in an expedient embodiment.
Eine Pumpvorrichtung für den Einsatz in einem Flugzeug-Kraftstofftank gemäß der Erfindung ist gekennzeichnet durch eine Kreiselpumpe mit einer Einrichtung zum Abscheiden eines in der Pumpe beim Betrieb aus dem von der Pumpe geförderten flüssigen Kraftstoff gebildeten Dampfeinschlusses sowie einen mit einem Ausgang der Dampfabscheideeinrichtung verbundnen Kanal, der auf einem im Betrieb im Bereich des Tankbodens liegenden Abschnitt mit einer Vielzahl von Durchlässen versehen ist.A pumping device for use in an aircraft fuel tank according to the invention is characterized by a centrifugal pump with a device for separating a vapor inclusion formed in the pump during operation from the liquid fuel delivered by the pump, as well as a connected to an outlet of the vapor separator Channel, which is located on a section in operation in the area of the tank bottom with a plurality of passages is provided.
Die ßrfindungsgemäße Pumpvorrichtung wird nachstehend anhand eines Ausführungsbeispiels in Verbindung mit der zugehörigen Zeichnung erläutert. In der Zeichnung zeigen!The pumping device according to the invention is described below using an exemplary embodiment in conjunction with the associated Drawing explained. Show in the drawing!
Fig. 1 einen Querschnitt durch eine Pumpvorrichtung und Fig. 2 eine Teilansicht entsprechend dem Pfeil 2 in Fig. 1.1 shows a cross section through a pump device and FIG. 2 shows a partial view according to arrow 2 in FIG. 1.
Lu/g ■Lu / g ■
27 11827 118
309837/0505309837/0505
2.31 H562.31 H56
In Fig. 1 1st rait 10 ein Kraftstofftank bezeichnet, der z. B.ein Tragflächentank sein kann und eine Kreiselpumpe 11 enthält. Die Kreiselpumpe 11 besitzt einen Rotor 12., der einen Teil des Rotors eines elektrischen Induktionsmotors darstellt. Der Rotor 12 enthält ein Paar von kegelstumpfförmigen Bauteilen 13 und 14, die im Betrieb dazu dienen, einen Luf t/Dampf -Eins ehluß in der Kreiselpumpe 11 abzuscheiden, der sich aus dem zu einem Ausgang 15 geförderten flüssigen Kraftstoff gebildet hat. Luft und Dampf in den Bauteilen 13 und \K werden über einen weiteren Ausgang 16 in einen Kanal 17 abgeführt. Der Kanal YJ weist einen Abschnitt 18 auf, der in Pig. 2 näher dargestellt ist und dicht am Boden des Kraftstofftanks 10 liegt. Der Abschnitt. 18 ist mit Durchlässen 19 versehen, durch die Luft und Dampf nach oben durch den im Kraftstofftank 10 befindlichen Kraftstoff hindurch austreten können.In Fig. 1 1st rait 10 denotes a fuel tank z. B. can be a wing tank and contains a centrifugal pump 11. The centrifugal pump 11 has a rotor 12, which is part of the rotor of an electric induction motor. The rotor 12 contains a pair of frustoconical components 13 and 14 which, during operation, serve to separate an air / vapor -Eins ehluß in the centrifugal pump 11, which has formed from the liquid fuel delivered to an outlet 15. Air and steam in the components 13 and \ K are discharged into a channel 17 via a further outlet 16. The channel YJ has a section 18 which is shown in Pig. 2 is shown in more detail and lies close to the bottom of the fuel tank 10. The section. 18 is provided with passages 19 through which air and steam can exit upward through the fuel in the fuel tank 10.
Der Abschnitt 18 ist netzförmig ausgebildet und bedeckt den größeren Teil des Bodens des Kraftstofftanks 10, so daß aus den Durchlässen 19 kommende Luftblasen durch den größten oder nahezu größten teil des in dem Kraftstofftank 10 befindlichen Kraftstoffes hindurchgeleitet werden. Der aus den Durchlässen 19 austretende Kraftstoffdampf wird von dem flüssigen Kraftstoff wieder aufgenommen. Die Luftblasen reißen die bereits im Kraftstoff gelöste Luft mit und tragen diese zur Kraftstoffoberfläche 20.The portion 18 is formed in the form of a network and covers the greater part of the bottom of the fuel tank 10, so that from The air bubbles coming through the passages 19 through the largest or almost the largest part of the air in the fuel tank 10 Fuel are passed through. The fuel vapor emerging from the passages 19 is replaced by the liquid fuel resumed. The air bubbles carry away the air that has already been dissolved in the fuel and carry it to the surface of the fuel 20th
Luft ,und Dampf, die sich im Kraftstofftank 10 oberhalb der Oberfläche 20 befinden, können über ein Entlüftungsventil entweichen.Air and steam that are in the fuel tank 10 above the Surface 20 are, can escape via a vent valve.
309837/0505309837/0505
Claims (2)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1118472A GB1412964A (en) | 1972-03-10 | 1972-03-10 | Aircraft fuel tank assemblies and pump arrangements therefor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE2311456A1 true DE2311456A1 (en) | 1973-09-13 |
Family
ID=9981565
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DE19732311456 Pending DE2311456A1 (en) | 1972-03-10 | 1973-03-08 | PUMPING DEVICE FOR AIRPLANE FUEL TANKS |
Country Status (6)
| Country | Link |
|---|---|
| JP (1) | JPS492102A (en) |
| DE (1) | DE2311456A1 (en) |
| ES (1) | ES412433A1 (en) |
| FR (1) | FR2175847B1 (en) |
| GB (1) | GB1412964A (en) |
| IT (1) | IT979759B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3964885A (en) * | 1974-06-18 | 1976-06-22 | Joseph Lucas (Industries) Limited | Centrifugal pumps |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB201012988D0 (en) | 2010-08-03 | 2010-09-15 | Airbus Operations Ltd | Dehydration of liquid fuel |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB597402A (en) * | 1944-12-21 | 1948-01-26 | Miles Lowell Edwards | Improvements in or relating to pumps |
| FR505389A (en) * | 1917-07-18 | 1920-07-29 | Gnome Et Rhone Moteurs | Further training in centrifugal pumps |
| FR515201A (en) * | 1920-05-06 | 1921-03-26 | Waldo A Ross Company | Method and apparatus for extinguishing fires in and around oil tanks |
| US2693148A (en) * | 1949-05-13 | 1954-11-02 | Vadolt Trust | Impulse feed pump for aircraft |
| GB686102A (en) * | 1949-09-09 | 1953-01-21 | Self Priming Pump & Eng Co Ltd | Improvements in or relating to pumps |
| FR1074689A (en) * | 1951-12-14 | 1954-10-07 | Self Priming Pump & Eng Co Ltd | Improvements in the production of centrifugal pumps |
| GB735866A (en) * | 1952-02-15 | 1955-08-31 | Rolls Royce | Improvements in or relating to fuel pumps and systems |
| FR2087270A5 (en) * | 1970-05-13 | 1971-12-31 | Lucas Industries Ltd |
-
1972
- 1972-03-10 GB GB1118472A patent/GB1412964A/en not_active Expired
-
1973
- 1973-03-08 IT IT48664/73A patent/IT979759B/en active
- 1973-03-08 ES ES412433A patent/ES412433A1/en not_active Expired
- 1973-03-08 DE DE19732311456 patent/DE2311456A1/en active Pending
- 1973-03-09 FR FR7308489A patent/FR2175847B1/fr not_active Expired
- 1973-03-10 JP JP48027644A patent/JPS492102A/ja active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3964885A (en) * | 1974-06-18 | 1976-06-22 | Joseph Lucas (Industries) Limited | Centrifugal pumps |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS492102A (en) | 1974-01-10 |
| FR2175847A1 (en) | 1973-10-26 |
| FR2175847B1 (en) | 1976-05-21 |
| ES412433A1 (en) | 1976-01-01 |
| IT979759B (en) | 1974-09-30 |
| GB1412964A (en) | 1975-11-05 |
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