Showing papers on "Ram air turbine published in 1969"

Gas turbine unit for generating mechanical energy and compressed air

Abstract: A gas turbine aggregate, especially an auxiliary unit for aircrafts which is intended to produce both mechanical energy and compressed air for loads, and in which a line branching off from the compressed air line that is supplied with compressed air from the compressor, leads to an air turbine which, in its turn, is connected with the output shaft of the gas turbine either directly or indirectly; the branch line from the compressed air line to the air turbine is provided with a valve to enable selective opening and closing of the branch line.

A modification to a variable shear stress air turbine viscometer

Abstract: A concentric cylinder air turbine viscometer previously described has been modified to extend the lower limit of shear stress to the region of 02 dyn cm−2. The effect of bearing pressure on calibration has been investigated.

Advancement of high-temperature turbine technology for small gas turbine engines fluid-cooled axial flow turbine

Abstract: : The report presents the results of an investigation directed toward the design and demonstration of a fluid-cooled turbine for an advanced small gas turbine. The primary objective was to advance and demonstrate high turbine inlet temperature technology for small gas turbine engines to the level that would provide a potential for doubling the specific horsepower relative to current small aircraft propulsion engines. While all major goals were met, providing the fluid-cooled turbine concept using a thermosiphon system to be valid, difficulty was encountered while attempting to provide 213 horsepower per pound of air for a free turbine.

Orbitally driven grinding apparatus

Abstract: A turbine driving means for the spindle of an orbital grinding machine. A standard air turbine is fixed to the spindle for following the orbital path and maintaining a given alignment and the grinding tool is positioned on the output shaft of the turbine.

Improvements in Gas Turbine Systems

Abstract: 1,165,537. Gas turbine plant; power plant. COAL INDUSTRY (PATENTS) Ltd. Jan. 10, 1967 [Jan. 11, 1968; March 8, 19661, Nos. 1266/66 and 10141/66. Headings F1G and F1Q. A gas turbine plant comprises a hot air turbine, the air being heated by being brought into heat exchange relation with the products of combustion of a fuel in the presence of a fluidized bed of solid particles, at least some of the heated air, after expansion in the turbine, providing a source of fluidizing gas for the fluidized bed. In Fig. 1 a hot air turbine 11 drives an air compressor 12 also an electric generator 13, air from the compressor passing through line 19 to the cold pass 16A of the fluidized bed heat exchanger 16, the air after being heated passing through line 20 to the hot air turbine 11. The air discharging from the turbine passes through line 17 to the combustion chamber 16B which constitutes the hot pass of the fluidized bed heat exchanger, the combustion gases from the chamber 16B finally discharging through outlet 18. Water is passed through line 21 into the second cold pass 16C of the heat exchanger, the steam produced passing through line 22 to a steam turbine 14. In Fig. 2 two fluidized bed heat exchangers, 16 and 23 are provided, combustion gases from a separate combustion chamber 24 passing first to the heat exchanger 16 then through line 25 to the second heat exchanger 23. Air from the compressor 12 passes through line 19 to the second heat exchanger 23, the air then passing through line 26 to the first heat exchanger 16, the heated air then passing through line 20 to the air turbine 11. The air discharging from the turbine passes through line 17 to the combustion chamber 24, a portion of the air being taken off through line 17A to the fluidized bed of the heat exchanger 23, and a second portion being taken off through line 17B to the fludized bed of the heat exchanger 16.

Improvements in or relating to Multiple Flow Gas Turbine Jet Engines

Abstract: 1,171,966. Jet propulsion engines. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION, Oct.30, 1967 [Jan. 11, 1967], No.49217/67. Heading F1J. A multiple-flow gas turbine jet engine comprises, in addition to a conventional compressor set driven by the usual gas turbine of the engine, one or more further compressors which are mechanically independent of the conventional commpressor set and of the usual gas turbine and are driven by an additional air or gas turbine located in the secondary (i.e., by-pass or fan) flow of the engine. In the engine shown in Fig.1, comprising an L.P. compressor 1 driven by an L.P. turbine 6a and an H. P. compressor 4 driven by an H.P. turbine 6b, the L.P. compressor supplying air not only to themain duct 2 but also to a by-pass duct 3, an intermediate-pressure compressor 11 is provided in the main duct 2 and driven by an air turbine 12 located in the by-pass duct 3 and provided with adjustable stator blading 12a. There may be two or more intermediatepressure compressors rotating in the same or opposite directions and each driven by its own air turbine. An auxiliary combustion chamber may be provided immediately upstream of the turbine 12. The compressor 4 and turbine 6b may be omitted.

Drive for Spindles of Textile Machines

Abstract: 1,164,612. Bearings. ERNEST SCRAGG & SONS Ltd. 20 Jan., 1967 [31 Jan., 1966], No. 45205/65. Heading F2A. [Also in Divisions D1 and H2] A false twist spindle (Division D1) is driven by an air turbine having air bearings. The rotor 15 is driven by tangential jets 27 from an air supply 24 which also feeds air bearings 17, 18 on the end faces of the rotor and air bearings 22, 23 on the spindle. The jets 27 and bearings 17, 18, 22, 23 are fed from a common source 27 by channels 25, 26.

Improvements in or relating to Fluid-Supply Systems Utilising a Bleed from an Engine or Compressor

Abstract: 1,157,962. Ventilating aircraft. PLESSEY CO. Ltd. 28 Sept., 1966 [8 Oct., 1965], No. 42738/65. Heading F4V. [Also in Division F1] The invention relates to an air supply system in which air is tapped for example from two different points of a compressor of a gas turbine engine for use for aircraft cabin pressurization. The air tapped from one point of the compressor is at a pressure greater than the required air pressure and that tapped from the other point is at a pressure less than the required air pressure. The air at the higher pressure is passed to an air turbine while that at the lower pressure is supplied to an air compressor driven by the air turbine, the air discharging from the turbine and that discharging from the compressor being mixed and thence supplied to the point of use. In the embodiment shown a chamber 5 is provided and an assembly comprising a rotor 1 and shaft 2 is rotatably mounted therein. The rotor 1 comprises a centrifugal air compressor 3 and an air turbine 10. High pressure air tapped from the engine compressor is supplied through line 7 and passes by way of a control unit 8 through lines 13 to nozzles 9 which direct it on to the air turbine. Lower pressure air tapped from the engine compressor passes through duct 4 to the air compressor 3, the air delivered by the compressor and that discharged from the turbine mixing in the chamber 5 and then passing through line 6 to the point of use. The control system for the turbine comprises a piston 11 disposed in a cylinder 12 the axial position of the piston determining the number of lines 13 and hence turbine inlet nozzles 9 through which high pressure air may flow. The piston 11 is connected to a piston 14 disposed in a cylinder 15, the piston 14 being subject at its right-hand side to pressure of the high pressure air in line 7 so that the pistons 11 and 14 are pressure balanced. The rod connecting the pistons 11 and 14 is connected to a control piston 16 disposed within a cylinder 17, one side of the piston being subject to ambient pressure and the other side being subject to pressure within the chamber 5. The excess of chamber pressure over atmospheric pressure thus tends to move the piston 11 to the left against the loading of spring 18, so as to cut off the number of turbine nozzles 9, so that less air is tapped through the line 7 and the power of the turbine 10 is reduced. Thus the pressure within the chamber 5 and so the air supplied to the cabin is reduced.

A Power Plant.

Abstract: 1,152,571. Air turbine plant; pneumatic power transmission. WHARNCLIFFE M. L. E. M. COUNTESS OF. Sept.15, 1966 [June 21, 1965], No. 26049/65. Headings F1G, FIT and F1X. [Also in Division H2] A power plant comprises an engine, such as an I. C. e. g. diesel engine 1, having two drive shafts 3, 4 which drive respective shafts 5, 12 mounting suctions and blowing fans 11,15 within the two ends of a casing 8 through which they impel air in a space 10 surrounding an electric generator 9 whereby the generator is driven by an air turbine 17 secured to the shaft 16. There may be further turbines 18, 20 on the shaft 16, a wire mesh screen filter 21 on the casing intake end, and coupled to the casing rear end one or more similar generators drives by the air from the casing 8. In another embodiment Fig. 1 a starting donkey (100) drives two I. C. engines (101, 102), and the suction fan axle (104) has a flywheel (105); this embodiment is stated to drive an aircraft by means of one or more bladed motors supplied by the generator.