Test Rig for Evaluating Active Turbine Blade Tip Clearance Control Concepts

High speed wear testing of an abradable coating

“…It is likely that the differences in behaviour, when compared to, for example, chip formation in conventional high speed machining of metal, are due to the low rate incursions of the blade tip into the abradable lining, as well as the specific properties of the materials involved. As designers of turbo-machinery look to include active blade tip clearance devices [9], these micro-rubs will become the dominating wear mechanism. Researchers have suggested that a compressive mechanism may occur, whereby the blade tip compresses the abradable lining and upon rebound, wear particles are released [10].…”

Dynamic probabilistic design approach of high-pressure turbine blade-tip radial running clearance

“…and Y c (t) are the radial deformations of turbine disk, turbine blade and turbine casing at time t, respectively, the variation τ (t) of BTRRC could be calculated [3][4][5][6] …”

“…Most previous efforts in the BTRRC design of gas turbine are completed from a deterministic analysis prospective [3][4][5][6][7][8][9][10][11]. The deterministic method cannot quantitatively trade off the two aspects (the reduction of blade-tip clearance and no friction) of the contradictory owing to no considering the randomness of various parameters influencing the clearance.…”

“…The loads and constraint conditions on the surface of turbine disk are axisymmetric and air-cooled. The temperatures of A1, A2, A3, B1, B2 and B3 on disk model were computed according to the boundary conditions of heat transfer [3][4][5][9][10][11]. In blade FE model, the tenons of turbine blade was simplified and reassigned on the disk model.…”

“…Therefore, only the bushing ring was analyzed, and its axial section was studied. The surface coefficients of heat transfer of three objects were calculated by the heat transfer characteristics in [3][4][5][7][8][9][10][11]. …”