Supercritical CO2 gas turbines for high-power generation

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Supercritical CO2 gas turbines for high-power generation ( supercritical-co2-gas-turbines-high-power-generation )

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Here – specific volume at the vane grid exit, – fluid velocity at the vane grid exit, – flow angle at the vane grid exit, – flow coefficient. This effect increases the stage tip losses and hurts the counter-pressure turbine efficiency. Therefore, the gain in axial dimensions causes the efficiency losses. The first stage presents an especially complicated problem because at the considered initial parameters the carbon dioxide specific volume at the vane exit is very small. At the same time, according to the equation (1), with an increase of the diameter , the enthalpy drop and the velocity grows accordingly. This contradiction between the Allam cycle turbine price and its efficiency is emphasized by the carbon dioxide specific volume twice smaller than the steam one. This difference may be balanced at acceptable vane height by twice larger carbon dioxide massflow than the steam turbine flow. This is followed by a drastic increase of the turbine power. In other words, the turbine power must be considerably high in this cycle. The reasons above determined for the parametric study the turbine power Nэ = 400 MW. The flowpath losses caused by the short vanes and blades are balanced by the flow increase. Together with this, the study thoroughly considers the tip losses mitigation. According to [4] the endwall losses structure is the following: (3) where – relative height expressed as a ratio to the axial chord , – relative pitch, and –inlet and outlet flow angles, – Reynolds number for the relative velocity of the flow exit, – relative coefficient equal to 1.9 for active stages and 0.7 for reactive stages. The first equation (3) member reflects losses concerned with friction in the endwall surfaces. The second member reflects the losses from secondary flow and tip stall swirls. The first member losses cannot be mitigated, but the second ones may be remarkably reduced by reduction of the reduced relative pitch near endwall by ithe ntroduction of curved ribs with height comparable to the hickness of the endwall boundary layer. Figure 3 illustrates this solution by results of a blade row flow test, curve 1 shows losses distribution without ribs, curve 2 – with ribs. FIGURE 3. Distribution of local energy losses coefficient along the height of the blade row [5] In the figure, it is seen that in the ribbed blade row channel the endwall losses are practically absent. The energy total loss coefficient in this blade row is 1.7% lower and the absolute losses are 30 % lower than in the initial blade row. 020026-4

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