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Patented Dec. 8, 1953 2,61,593 UNITED STATES PATENT OFFICE 2,661,593 MOUNTING 0F GAS TURBINE UNITS John Oliver Philip Hughes and Paul Heinz Walter Wolif, Rugby, England, assignors to The Eng lish Electric Company Limited, London, Eng land, a British company ApplicationSeptember2,1949,SerialNo.113,883 Claims priority, application Great Britain September8,1948 . 6Claims. (Cl.60-3931) 2 Fig. l is a side elevation of a gas turbine unit. Fig. 2 is an end elevation thereof as seen in the direction of the arrow A of Fig. 1. According to the invention a rigid unit, con sisting of at least one turbine and compressor therefor, is attached by means of metal bonded ' rubber bushings arranged substantially in one plane at or near the centre of gravity of the said unit, transverse to the axis thereof, preferably, but not necessarily, with an auxiliary metal 10 gas turbine set, on the same scale as Fig. 3. The invention relates to the mounting of gas turbine units in general, and in gas turbine driven locomotives in particular. bonded rubber ‘bushing or bushings arranged in a direction parallel to the axis of the unit at or near one end of the unit. As metal bonded rubber bushings offer a com Fig. 5 is a side elevation of a gas turbine unit. Fig. 6 is an end elevation thereof as seen in the direction of the arrow A of Fig. 5. Fig. '7is a horizontal cross section on the line parativelyhighresistancetodeflectioninadi 15l’-lofFig.5throughoneofthehorizontal rection perpendicular to their axis (which is taken by the rubber in compression and tension, respectively) than in the direction of their axis (Which is taken by the rubber in shear), such an arrangement provides a good location of the 20 and 6 seen in the same directions as on these set in alignment with its output shaft while allowing for the thermal expansion of the set in operation. As the metal bonded rubber bushings preserve theirdesirableresilientanddampingcharacter 25 No. 76,335 ?led on February 14, 1949, now istics only up to a certain maximum tempera ture, say 70° C., the metal bonded rubber bush ings or at least some of them, are cooled accord ing to a preferred subsidiary feature of the in vention. According to a development of the invention, a gas turbine unit comprising a heat exchanger the hot pass of which is passed by the exhaust gases of the turbine, and the cold pass of which abandoned, comprising a multi-stage compressor arranged in a casing 56, I2 coupled with a gas turbine driving it and arranged in a casing 53, with an independent power output turbine ar ranged in alignment therewith in the casing 54. 29 is the air intake into‘ the compressor at the front end of the set, 50 the compressed air duct from the compressor output to the top of the heat exchanger i, 62 are the two sym metrically arranged combustion chambers con is passed by the compressed air on its way from the compressor to the combustion chamber, is 35 nected with the bottom of the heat exchanger suspended as a whole in the manner hereinabove described, the heat exchanger being attached to the said unit at its front by means of the com pressed air pipes from the compressor and to the combustion chambers, and at its rear to the horizontal radial engine bearers of the said unit by means of cantilever booms rigidly connected to these attachments and extending towards the rear end of the heat exchanger which rests on them by means of a spring having a ?at load deflection characteristic, and preferably also of metal bonded rubber cushions, the suspension allowing a horizontal movement of the said heat exchanger with respect to the said booms at their points of connection. In order that the invention may be better understood and readily carried into eifect, some embodiments thereof will now be described by way 0f example with reference to the accompany ingdrawings,inwhich: 5! and, by the elbows 52, with the entrance l2a of the gas turbine casing 53, 55 is the turbine‘ exhaust elbow connected with the bottom of the heat exchanger, and 28 is the discharge funnel therefrom. This gas turbine unit issupported in the metal bonded rubber bushings i, 2 and 3 radially ar ranged with respect to the axis of the unit in a vertical plane substantially through the centre 45 of gravity C. G. of the unit. By the reasons given above, these bushings offer comparatively little resistance to radial thermal expansions of the turbine casing while they effectively restrain this casing from turn 50 ingaboutitsaxis,movingforeoraft(thesetwo movements being resisted by all three bushings I, 2‘and 3), up or down or yawing' about a ver tical axis (restricted by the bushings I and 2), and right or left or pitching about a transverse 55 axis(resistedbythebushing3). Preferably there is an additional metal bonded Fig. 3 is a cross section on the line 3—3 of Fig. 1 through one of the horizontal radial engine bearers of the gas turbine unit on a larger scale. Fig. 4 is a longitudinal section through the sub sidiary engine mounting at the front end of the radial engine bearers of the gas turbine unit on a larger scale. Fig. 8 is a side elevation, and Fig. 9 is an end elevation of a detail of Figs. 5 ?gures but on a larger scale. Referring ?rst to Figs. 1-4, the gas turbine of this embodiment (Figs. 1 and 2) is of the kind forming the subject of patent application Ser.PDF Image | MOUNTING OF GAS TURBINE UNITS
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