The blade surfaces of the integral impeller and blisk are functional surfaces for power transmission, and their surface integrity has significant effects on the aerodynamic efficiency and service life of an aero- engine. The integral impeller and blisk of an aero- engine are high performance parts with complex structure and made of difficult-to-cut materials. Machining the Integral Impeller and Blisk of Aero- Engines: A Review of Surface Finishing and Strengthening Technologiesįu, Youzhi Gao, Hang Wang, Xuanping Guo, Dongming
In addition, there are no widely used repair methods.Despite these disadvantages the usage of bimetallic turbine blisks with shrouded blades is very promising. The shortcoming is elimination of damping in root connection. Application of bimetallic blisks with shrouded blades resulted in a lifespan increase and weight reduction.In addition, other advantages of blisk design are as follows: possible reduction in the number of parts, elimination of leaks and fretting that take place in the blade - disk locks, exception of expensive broaching operations and disk alloy saving. Numerical studies of the influence of the shroud mounting position on blade strength during operation allowed us to develop a methodology of choosing a shroud mounting position.Based on the two turbine wheels (LPT and HPT calculations advantages of blisk design with respect to the lock-based design were shown. It is necessary to increase efficiency and to improve high cycle fatigue performance of rotor blades.One of the pressing problems is to ensure the necessary position of shrouds in relation to each other in the manufacturing process as well as in the service. This technology allows us to use blades with shrouds.
But design engineers are faced with the problem of blade placement because of the disk size and root dimensions.The problem of increasing life and cyclic durability, vibration strength, and lightweight design of the turbine gas turbine wheels, can be solved by an elimination of blade - disk locks.The technology of manufacturing one-piece blisks by connecting the blades with the disc part using hot isostatic pressing was developed. Increasing an engine life and efficiency as well as mass reduction can also be achieved by increasing blade numbers and decreasing disk diameter. A nacelle provides an outer flow duct for the thrust fan blades and a secondary flow duct carries flow from the integral secondary flow blades as cooling air for components of the reverse flow turbine engine.īimetallic Blisks with Shrouded Turbine Blades for Gas Turbine Enginesĭirectory of Open Access Journals (Sweden)įull Text Available The paper discusses prospects of using blisks with shrouded blades. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral secondary flow blades extending intermediate an inner hub and the outer hub. Secondary air flow is provided for a ducted fan having a reverse flow turbine engine core driving a fan blisk. Reverse Flow Engine Core Having a Ducted Fan with Integrated Secondary Flow Blades
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