Patent RU-2757245-C1 (RU)
Title: Nozzle apparatus of a high-pressure turbine of a gas turbine engine
Inventor: Kuzmin Maksim Vladimirovich
IPC: F01D5/18
Filed: 2020-07-23
Granted: 2021-10-12
Abstract: FIELD: engine building. 
     SUBSTANCE: nozzle apparatus (NA) of a high-pressure turbine (HPT) of an aviation gas turbine engine (GTE) comprises an outer and an inner rings of the nozzle apparatus connected with an outer and an inner bodies of the combustion chamber, respectively, a nozzle blade crown with external and internal shelves connected with the outer and inner rings of the nozzle apparatus, respectively, wherein a longitudinal cooling channel is made in each vane of the nozzle blades, communicating with the cavity formed by the outer ring of the nozzle apparatus and the outer body of the combustion chamber with air bypass valves, as well as with the cavity for air supply to the twisting apparatus, made in the inner ring of the nozzle apparatus, wherein, according to the present invention, the cooling channel of each of the blades communicates with the cavity formed by the outer ring of the nozzle apparatus and the outer body of the combustion chamber with air bypass valves by means of two sleeves connected telescopically with a possibility of mutual radial displacement, wherein one of the sleeves is installed in a hole of the outer ring of the nozzle apparatus and fixed relative to the outer ring by means of two diametrically opposed protrusions made on the outer surface thereof, passed into the annular grooves of the outer ring of the nozzle apparatus made from the side of the outer diameter of the latter, as well as a lock washer, and the other sleeve is made from the side of the outer surface of the outer shelf of the nozzle blade integrally therewith, wherein the cooling channel of each of the nozzle blades communicates with the cavity for air supply to the twisting apparatus by means of a tubular element fixed in the hole of the internal ring of the nozzle apparatus by means of a hinged connection and a sleeve made from the side of the inner surface of the inner shelf of the nozzle blade integrally therewith and connected with the tubular element by means of a hinged connection, the outer shelves of the nozzle blade crown are also fixed in the outer ring of the nozzle apparatus in the radial direction by means of an L-shaped projection made on the outer surface of each of the outer shelves of the blades from the side of the trailing edge of the vane, inserted by the end section into the annular groove of the outer ring made from the side of the inner diameter of the latter, as well as two U-shaped protrusions made on the outer surface of each of the outer shelves of the blades from the side of the trailing edge of the vane, spaced relative to each other in the circumferential direction, passed into the grooves whereof is the face part of the outer ring, wherein an annular groove is made on the outer diameter of the inner ring of the nozzle apparatus, and a mating groove is made from the side of the inner surface of each of the inner shelves of the nozzle blade crown, installed wherein is an annular elastic element shutting off the air flow from the high-pressure compressor to the flow section of the high pressure turbine. 
     EFFECT: increased reliability, reduced weight, and simplified design of the NA are achieved. 
     1 cl, 3 dwg