GB1060097A - Improvements relating to the flow of a cooling fluid - Google Patents

Abstract

1, 060, 097. Gas turbine engine combustion equipment. ROLLS-ROYCE Ltd. May 6, 1965 [May 13, 1964], No. 19804/66. Divided out of 1, 060, 095. Heading F1L. The invention relates to an assembly comprising inner and outer tubular members which are telescoped into each other with an annular space therebetween, the invention being described with reference to gas turbine engine combustion equipment which comprises outer and inner air casings 11, 12 Fig. 1 (not shown), which define an annular space in which are disposed a series of flame tubes. Each flame tube comprises a series of sections 14, 15, 16, 17 which telescope one into the other to define annular air spaces 26, 27, 28 therebetween. In Fig. 2 the flame tube sections 14, 15 are formed integrally with a radially extending wall 40 and a series of radiallyextending holes 42 are formed in the flame tube section 15 being adapted for the flow therethrough of cooling air which then flows axially through the annular space 26 to effect film cooling of the inner surface of the tube section 15. Means are provided for reducing the tendency of the cooling film to break away from the surface of the section 15, which means in Fig. 2 comprises a series of axially-extending holes 41 formed in the radiallyextending wall 40 for the flow of cooling air therethrough, the holes 41 being axially-aligned with the radial holes 42. In a second embodiment the axial holes 41 are not in alignment with the radial holes 42. In further embodiments, the part 20 of the tube section 14 converges towards the tube section 15 so that the annular space 26 is of convergent form. In a further embodiment the annular space 26 is again of convergent form but the axially-extending holes 41 in the radial flange 40 are not provided.