GB841320A - Improvements in or relating to engine mountings - Google Patents
Improvements in or relating to engine mountingsInfo
- Publication number
- GB841320A GB841320A GB10811/56A GB1081156A GB841320A GB 841320 A GB841320 A GB 841320A GB 10811/56 A GB10811/56 A GB 10811/56A GB 1081156 A GB1081156 A GB 1081156A GB 841320 A GB841320 A GB 841320A
- Authority
- GB
- United Kingdom
- Prior art keywords
- struts
- sleeve
- flange
- engine
- brackets
- 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
- 239000002184 metal Substances 0.000 abstract 1
Classifications
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/04—Aircraft characterised by the type or position of power plants of piston type
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
841,320. Engine mountings for aircraft. ROLLS-ROYCE Ltd. April 5, 1957 [April 9, 1956], No. 10811/56. Class 4. [Also in Groups XXVI and XXXII] An engine mounting for attaching an engine component 11 (stated in the preferred embodiment to be an annular oil tank which encircles the compressor casing of a propeller-driving gas-turbine engine) to part 10 of an airframe bulkhead comprises four similar flexible mounting devices 12 each secured to component 11 by lugs 17 and pairs of struts 19 and brackets 20, and to part 10 by pairs of struts 31 and brackets 33. The connections between struts 19 and devices 12 and brackets 20 comprise partspherical connections which may be locked in selected positions and the lengths of the struts may be adjusted, to suit individual engines. Each device 12, which also may be angularly adjusted to suit individual engines, comprises an outer sleeve 13 and an inner sleeve 25 bonded to a rubber bushing 22. Sleeve 13, which is secured to struts 19, has an end wall 14 formed with attachment lugs 15 and an opposed flange for the attachment of a collar member 24 formed with an annular flange 24a which limits excessive axial movement of sleeve 25. A metal liner 21, bonded to the outer surface of bushing 22, is clamped axially between a flange 23 on sleeve 13 and the member 24. Sleeve 25 is provided internally with a frustoconical flange 26 formed on its internal surface with a part-spherical seating 27 which cooperates with a part-spherical surface 28 on a collar 29 fitted over the cylindrical end of a tapered extension of a member 30 to which struts 31 are attached. Washers 35 of selected thickness may be fitted to ensure that devices 12 lie in a common plane. The faces 27 and 28 are maintained in contact by a bolt 36 and nut 37, which has a splined connection with member 30. In a further embodiment, the cylindrical seating for collar 29 is formed on the flange 26 and the part-spherical surface 28 on the end of the conical extension of member 30.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB10811/56A GB841320A (en) | 1956-04-09 | 1956-04-09 | Improvements in or relating to engine mountings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB10811/56A GB841320A (en) | 1956-04-09 | 1956-04-09 | Improvements in or relating to engine mountings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB841320A true GB841320A (en) | 1960-07-13 |
Family
ID=9974709
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB10811/56A Expired GB841320A (en) | 1956-04-09 | 1956-04-09 | Improvements in or relating to engine mountings |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB841320A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5746391A (en) * | 1995-04-13 | 1998-05-05 | Rolls-Royce Plc | Mounting for coupling a turbofan gas turbine engine to an aircraft structure |
| US7748661B2 (en) | 2005-12-21 | 2010-07-06 | Airbus Uk Limited | Aircraft structure and a fastener for use therewith |
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
-
1956
- 1956-04-09 GB GB10811/56A patent/GB841320A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5746391A (en) * | 1995-04-13 | 1998-05-05 | Rolls-Royce Plc | Mounting for coupling a turbofan gas turbine engine to an aircraft structure |
| US7748661B2 (en) | 2005-12-21 | 2010-07-06 | Airbus Uk Limited | Aircraft structure and a fastener for use therewith |
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
| CN110844090B (en) * | 2019-10-11 | 2022-11-22 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
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