NOZZLE ASSEMBLY OF LOW-PRESSURE TURBINE (LPT) OF GAS TURBINE ENGINE (GTE) (VERSIONS) AND BLADE OF LPT NOZZLE ASSEMBLY (VERSIONS)

FIELD: aviation.SUBSTANCE: group of inventions relates to the field of aircraft engine building. LP turbine nozzle assembly comprises nozzle clusters mounted between outer and inner power rings connected by hollow power pins. Each of nozzle cluster is assembled from three rigidly connected blades made as a whole with small and large shelves. Power pins are passed through power rings and cavities of each extreme blade of the NC. Medium-length vane cavity of every cluster is furnished with LP turbine rotor air-flow passage pipe. Outer ring NA is made hollow, composed of ring elements to form input manifold of air cooling circuit NA. Front annular element is provided with flanges for detachable connection with TPE NA and housing of CS, and rear - for detachable connection with housing of LP turbine support. Outer ring is provided with at least two holes for passage of cooling air from AAHE to input manifold and at least eleven holes for air passage from collector into cavity of nozzle blades. Cylindrical elements of external and internal rings are equipped with openings for passage of power pins and tubes of transit path of air cooling of LP turbine rotor. Inner ring NA together with frontal conic diaphragm, made integral with body of bearing of support of TPE and rear conical diaphragm-cover, forms intermediate collector of transit path for air cooling of LP turbine rotor. Inner ring CA is equipped with annular seals with abutment to ends of small shelf of blocks with possibility of return radial displacements to compensate for difference of radial thermal deformations of NA elements. Blades are installed in the nozzle units at an angle towards the flow of the working medium and have a sail. Blade is made with angular swirling of the profile on the greater part of the blade height and with increase in height of the output edge relative to the input edge. Blade is provided with finning of the inner surface of the inlet edge and walls to support the deflector to form a stabilized height of the channel of the blade air cooling airflow between its walls and the deflector.EFFECT: higher efficiency and longer life of LP turbine nozzle assembly and engine.9 cl, 9 dwg Группа изобретений относится к области авиадвигателестроения. Сопловый аппарат ТНД двигателя содержит сопловые блоки, смонтированные между наружным и внутренним силовыми кольцами, соединенными полыми силовыми спицами. Каждый из сопловых блоков собран из трех жестко соединенных лопаток, выполненных за о