From the Rolls-Royce experimental archive: a quarter of a million communications from Rolls-Royce, 1906 to 1960's. Documents from the Sir Henry Royce Memorial Foundation (SHRMF).
Patent specification for improvements to aircraft propulsion using gaseous jet reaction.
| Identifier | ExFiles\Box 147\2\ scan0212 | |
| Date | 25th February 1938 | |
| PATENT SPECIFICATION Application Date: Feb. 25, 1938. No. 6037 / 38. 512,064 Complete Specification Left: March 25, 1939. Complete Specification Accepted: Aug. 29, 1939. PROVISIONAL SPECIFICATION Improvements relating to the Propulsion of Aircraft I, FRANK WHITTLE, a British Subject, of "Broomfield", Bilton Road, Rugby, Warwickshire, do hereby declare the nature of this invention to be as follows:— This invention relates to the propulsion of aircraft and more especially to propulsion by gaseous jet reaction, for example by constant pressure cycle gas turbine arrangements in conjunction with rearward jets. The present invention seeks primarily to increase propulsive efficiency. The invention consists primarily in a propulsive device including a combustion engine, which aspirates all or part of its air from the airstream passing close to the surfaces of the aircraft, preferably from those regions where the relative airflow has been retarded relative to the aircraft, commonly referred to as boundary layer air. The propulsive device is preferably one as described in my Patents Nos. 456,976, 456,980, or 471,368. It is proposed to abstract some of the boundary layer, for example over the wings and fuselage of an aeroplane and lead it by suitable means to the input side of a gaseous reaction apparatus, such for example as that described in Specifications Nos. 456,976, 456,980 or 471,368. As an example some of the input of air to the propulsion system may be derived from a fairly widespread series of orifices in the surface of a wing. Alternatively, the system may be incorporated in an aircraft in which the fuselage, or nacelles, housing the propulsive machinery, as well as any desired cabin or other accommodation, is of streamline form truncated at the rear end where the propelling jet emerges and circumferentially completely or partially around the fuselage or nacelle is an annular forwardly facing intake, at a distance say two-thirds to three-quarters of the total length back from the leading end, or in the zone where a considerable depth of boundary layer is found to be present. The intake may be formed by a hollow "false tail" or fairing piece of truncated conical form with its base directed forward and its truncated apex surrounding the jet. A single power unit aeroplane including these features comprises a mid-wind monoplane with a stream-lined nacelle-like fuselage accommodating the pilot and load well forward. This fuselage has, in rearward continuation of its upper part, a boom or tail extension carrying the empennage, and below this is truncated to provide for the emergence of the propelling jet. Within the fuselage is a compressor-turbine combination of the kind described in my previous (and above-referred-to) Specifications. This is supplied by a duct with air entering the annular intake practically completely surrounding the fuselage well behind its maximum cross-sectional dimensions. Its effluents or exhaust emerges through the jet. The fuselage (there being no consideration of airscrew clearance) may be supported on a single-wheel main undercarriage which is retractable, the wings having retractable skids for lateral balance when at rest. The arrangement favours the attachment of the wings at a relatively high angle of incidence, such wings being preferably used with any known means for increasing their lift co-efficient. Dated the 25th day of February, 1938. For the Applicant, F.{Mr Friese} J.{Mr Johnson W.M.} CLEVELAND & COMPANY, Chartered Patent Agents, 29, Southampton Buildings, Chancery Lane, London, W.C.2. COMPLETE SPECIFICATION Improvements relating to the Propulsion of Aircraft I, FRANK WHITTLE, a British Subject, of Broomfield, Bilton Road, Rugby, Warwickshire, do hereby declare the nature of this invention, and in what manner the same is to be performed, to be particularly described and ascertained in and by the following statement:— This invention relates to the propulsion of aircraft and more especially to propulsion by gaseous jet reaction, for example [Price 1/-] | ||