GB893111A - Pump assembly - Google Patents
Pump assemblyInfo
- Publication number
- GB893111A GB893111A GB3184458A GB3184458A GB893111A GB 893111 A GB893111 A GB 893111A GB 3184458 A GB3184458 A GB 3184458A GB 3184458 A GB3184458 A GB 3184458A GB 893111 A GB893111 A GB 893111A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pump
- tank
- fitting
- discharge
- top cap
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
Abstract
893,111. Centrifugal pumps. EDWARDS, M. L. Oct. 6, 1958, No. 31844/58. Class 110 (1). [Also in Group XXVIII] A submersible fuel pump P, Figs. 3 and 4, is inserted by means of a tool T into an aircraft fuel tank C through an access hole in the top wall of the tank. With the discharge conduit 12 of the pump in engagement with a discharge fitting F carried by the tank, the pump is rotated by means of the tool T to bring hook-like lugs 12f on the conduit 12 into the position shown in Fig. 3 in which they engage screws 40 on the discharge fitting F. Splined nuts 41 are then tightened by means of a socket wrench. Gas and vapour in the liquid entering the pump impeller 28 are expelled back to the tank through passages 24 and directed by a lip 25 away from the pump inlet. The pumped liquid passes through diffuser vanes 31 and then through an annular passage 13 to cool the motor M before entering the discharge conduit 12. In a modification, the discharge fitting F is attached to the bottom wall of the tank and is turned upwardly at an angle to receive the correspondingly downwardly-angled pump discharge conduit 12. In a further embodiment the discharge fitting F is integral with the top cap of the pump. The pump, with the top cap and fitting F bolted to it, is inserted into the tank through a hole in a side wall of the tank and the fitting F is then bolted to the tank around the hole. The pump can be unbolted from the top cap and dropped down from it for replacement without removing the top cap and fitting F from the tank. The pump shown in Fig. 10 is connected to the discharge fitting F by means of a pipe 174 and an elbow 188 and is supported partly by the fitting F and partly by the engagement of a spigot 178 with a supportmember 180. If the pump fails it is by-passed by a check-valve 177. In a modification, the discharge fitting F is attached to the top wall of the tank with the pump depending from it through a vertical pipe. The base of the pump engages a support-ring attached to the bottom wall of the tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3184458A GB893111A (en) | 1958-10-06 | 1958-10-06 | Pump assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3184458A GB893111A (en) | 1958-10-06 | 1958-10-06 | Pump assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB893111A true GB893111A (en) | 1962-04-04 |
Family
ID=10329238
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3184458A Expired GB893111A (en) | 1958-10-06 | 1958-10-06 | Pump assembly |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB893111A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3832093A (en) * | 1972-08-09 | 1974-08-27 | D Shirek | Portable pump |
| FR2962405A1 (en) * | 2010-07-06 | 2012-01-13 | Airbus Operations Sas | AIRCRAFT COMPRISING A FUEL PUMP ATTACHED TO A TANK PANEL |
-
1958
- 1958-10-06 GB GB3184458A patent/GB893111A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3832093A (en) * | 1972-08-09 | 1974-08-27 | D Shirek | Portable pump |
| FR2962405A1 (en) * | 2010-07-06 | 2012-01-13 | Airbus Operations Sas | AIRCRAFT COMPRISING A FUEL PUMP ATTACHED TO A TANK PANEL |
| US8851122B2 (en) | 2010-07-06 | 2014-10-07 | Airbus Operations (S.A.S.) | Aircraft including a fuel pump fastened to a tank panel |
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