FIELD: engines and pumps.
SUBSTANCE: turbine guide vanes sector comprises front and rear engagement means and wearproof device. Front engagement means rests on support mounted at turbine housing. Wearproof device is composed of a part from metallic material surrounding front engagement front end and fitted between front engagement means and said support to allow a sliding contact there between. Said wearproof means is retained in axial direction at vanes sector by fastener interacting with front engagement means. The other invention of proposed set relates to aircraft gas turbine engine turbine module with guide vanes composed by abode described sectors. One more invention relates to gas turbine engine incorporating said turbine module.
EFFECT: decreased wear.
14 cl, 8 dwg
