| 摘要 |
1,063,240. Turbine vanes and struts. UNITED AIRCRAFT CORPORATION. Dec. 2, 1965 [Dec. 7, 1964], No. 51187/65. Heading F1T. The invention relates to a turbine vane or strut which has associated therewith a heat shield whereby the rate of temperature change in the vane or strut during transient conditions is reduced. In the embodiment shown, the strut 2 is hollow and comprises a radially inner end portion 8, Fig. 1 (not shown) which is secured to inner stator structure comprising annular members 10 and 12, also a radially outer end portion 16 which is secured to outer stator structure comprising annular members 18 and 20. The strut is surrounded by a correspondingly shaped heat shield 24, Fig. 2 which is secured at the leading and trailing edges of the strut. A bracket 28 is secured by rivets 30 to the leading edge of the strut, the bracket being formed with a longitudinally extending recess 32 in which is received a projection 34 extending longitudinally within the leading edge portion of the heat shield 24. A rivet 54, Fig. 4 (not shown), secured to the bracket 28 towards the radially outer end thereof engages a recess 56 formed in the projection 34 to locate the heat shield. A bracket member 44 is also secured at the trailing edge of the strut, the bracket being formed with a projection 46 which is received within a recess 48 formed in the trailing portion of the heat shield. At the radially outer portion, the projection 46 is extended and is secured to the heat shield by means of rivets 52a, Fig. 3 (not shown). |
