Patent GB-695724-A (GB)
Title: Improvements in or relating to structural elements for axial-flow turbo-machines such as compressors or turbines of gas-turbine engines
Inventor: KENT NELSON HECTOR
IPC: D01F2/10
Filed: 1950-08-01
Abstract: 695,724. Turbines and compressors. ROLLS-ROYCE, Ltd. Oct. 26, 1951 [Aug. 1, 1950], No. 19179/50. Classes 110(i) and 110(iii) In an axial-flow machine such as a compressor or turbine, blades forming part at least of one or more blade stages are mounted in a shroud structure comprising a first annular or part-annular sheetmetal shell and a second annular or part-annular sheet-metal shell secured co-axially with the first shell and radially spaced therefrom, one end of each blade being mounted in aligned openings formed in the shells and secured by welding or brazing. In the gas turbine engine shown in Figs. 1 B  and 2, the shroud structure of the axial flow compressor comprises a first shell 19 forming part pf the working fluid annulus of the machine, and a second shell 20, channel-section rings 21 being secured at the ends of the inner shell 19 with the webs 21b radially disposed and the channels facing axially in opposite directions. Tabs 22 are disposed around the edges of the second shell 20 and pass through slits in the channel section rings and are secured thereto by brazing. The roots 23a of the stator blades 23 pass through the aligned openings 24 in the shells and are secured by brazing. The inlet nozzle structure of the turbine is shown at the right-hand side of Fig. 1B and comprises nozzle guide vanes 26 mounted in shroud structures at both ends, the inner and outer shrouds comprising respectively first shells 30, 27 and second shells 32, 29. The first shells have frustoconical portions 30b, 27b which are connected with forwardly extending portions 31, 25 of the second shells, the portions 31, 25 forming an air casing around the combustion chamber flame tube 28. The shells may also be spaced apart by means of a third shell member of the same axial extent as the first shell, the third shell being in contact with the first over its central portion and having radial flanges with axial extensions which contact the second shell. The third shell may alternatively be in contact with the second shell and have inward radial flanges with axial extensions in contact with the first shell. The first and second shells may alternatively be connected by Z-section rings, or by means of rows of dimples in the second shell which contact the first shell between blade rows. Again, the second shell may be corrugated, the troughs of the corrugations being in contact with the first shell between the blade rows. One or more stages of blades may be located in each of the structures, and the structures are preferably formed in semi-circular halves. The structures are disposed in an outer cylindrical casing 15 of the engine. The shroud structures may be located circumferentially by means of hollow tubes or rods 53, Fig. 5, which pass through the radial webs 21b of the channel-section rings 21, tubular distance pieces 55 being disposed between the webs 21b of the two rings of each structure, and distance pieces 56 being disposed between the webs of adjacent structures. In the embodiment shown in Fig. 5, the stator blades 23<SP>11</SP> support at their inner ends a bearing 57 for the rotor 59.