By Donna J. Ciafone
This ebook provides present examine within the learn of gasoline generators from around the globe. issues mentioned contain techno-economic reviews of fuel turbine repowering platforms; in-service degradation of gasoline turbine nozzles and relocating blades; the corrosion features of titanium dependent alloys and their degradation mechanisms optimisation of a regenerative fuel turbine strength plant and a dialogue of the fluid/solid coupled warmth move difficulties in gasoline turbine purposes.
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Additional resources for Gas Turbines: Technology, Efficiency and Performance
6 ºC) of S-P1 and S-P2, respectively. It was estimated that the ST TIT can be superheated from 280 ºC up to 491 ºC by utilizing the high temperature GT exhaust gas. 4%) of the STPS, respectively. 42 MPa), and this feature contributes to making heat energy loss at the condenser small for S-P1 and S-P2. The GT turbine axial power output of the S-C is estimated to be 1128 kW, but 706 kW is consumed for air compression, and hence the GT generator power output is estimated to be 400 kW. On the other hand, the HT turbine axial power output of the S-P1 is estimated to be 1086 kW, and only 187 kW is consumed for air compression work, and hence the HT generator power output is estimated to be 854 kW.
This is why this zone may be used as a reference zone. The blade root surface was etched by a solution of 10 % of perchloric acid (HCLO4) diluted in ethanol and then electro polished to reveal the microstructure. The microstructure of the transversal section of the root (see Figure 15) is shown in Figure 16. The microstructure consists of equiaxed grains of γ phase (alloy matrix) and fine particles of γ´ precipitated within the matrix. Also, dispersed particles of carbides in the grain boundaries and matrix were found.
The stresses with detrimental effect to the nozzle and blade were principally of thermal type, developed due to high temperature gradients across the airfoil wall. These generate thermal fatigue mechanism and high steady state load leading to creep mechanism. The dense and continuous net of carbides reduces ductility and toughness of alloy and facilitates crack initiation and propagation. The degradation of γ´ originates a reduced alloy creep lifetime and the degradation of alloy (matrix γ) due to grain coarse growing originates a reduced alloy fatigue lifetime.