| 摘要 |
1,024,959. Gas turbine engines. GENERAL ELECTRIC CO. Dec. 21, 1964 [Dec. 30, 1963], No. 51771/64. Heading FIG. The invention relates to a self-aligning mounting structure for a gas turbine engine within a generally cylindrical rigid container having an inlet and an outlet. An adjustable engine support is provided adjacent the inlet for supporting the compressor end of the engine. The inner side of the container outlet is provided with an annular seating surface and the outer side of the casing of the nozzle or outlet section of the engine is provided with a similar and abutting annular seating surface, the two seating surfaces being of part-spherical shape in crosssection. The invention is described with reference to the use of an aircraft type gas turbine jet engine as a gas generator for supplying gases to a power turbine in a stationary installation. The gas turbine engine 18, (Fig. 1 not shown), is disposed within a cylindrical outer casing 10 formed of a forward portion 12 and a rearward portion 14 secured together by a flanged joint 16. The air inlet to the engine is shown at 30 and the gas outlet at 32. The forward end of the engine is supported within the outer casing 10 by means of a turnbuckle 44 connected to a bracket 40 secured to the engine casing and to a channel section member 48 secured externally of the outer casing. There are preferably two such supports spaced 90 degrees apart. The rearward end of the engine is supported within the outer casing by mounting arrangement 50 shown in detail in Fig. 2. The rearward portion 14 of the outer casing is formed with a radially inwardly projecting flange 52 to which is secured by bolts 55 a mounting ring 56 formed with a part spherical seating surface 60. A frustoconical ring member 62 is secured at 66 to the engine casing 20, the rearward end of the ring member being formed with a flange 72 also with a part-spherical seating surface 70 which engages with the part-spherical seating surface 60 of the mounting ring 56. The engine casing 20 has secured thereto an extension piece 20a to which is secured a piece 20b which acts as a heat shield. A stiffener member 78 is provided between the two pieces 20a, 20b. The method of assembly of the engine within the outer casing is described. |
