Turbine Interstage Research Articles

Comparative study of multiple-mode collaborative operation strategy and traditional heat and power decoupling technologies for cogeneration system based on GTCC

This study proposes a multiple-mode collaborative operation strategy for the first time, which integrates compressor inlet air heating mode, gas turbine interstage extraction mode, and back pressure heating mode. This operation strategy can improve the peak shaving flexibility of the cogeneration system based on gas turbine combined cycle (GTCC). This article uses Ebsilon software to simulate cogeneration system based on GTCC under different heat and power decoupling technologies and obtain the heat and power operation region. The peak performance of different heat and power decoupling technologies on heating characteristic days are analyzed. Meanwhile, the impact of objective power load changes is studied. The results show that during the whole heating season, compared with the conventional operation mode without heat and power decoupling technology, the multiple-mode collaborative operation strategy, electric boiler (EB) technology, and heat storage tank (HST) technology are adopted, and the renewable energy integration of the cogeneration system based on GTCC are increased by 1.16 × 105 MW, 1.37 × 105 MW and 5.65 × 104 MW, respectively. In addition, When the objective power load is 197.5 MW or 120 MW, taking into account the integration of renewable energy, natural gas consumption, and system benefits, the multiple-mode collaborative operation strategy is the optimal choice.

Peak regulation performance study of the gas turbine combined cycle based combined heating and power system with gas turbine interstage extraction gas method

Improving the peak regulation performance of the gas turbine combined cycle (GTCC)-based combined heating and power (CHP) system helps to increase the integration of renewable energy. A new method of the gas turbine (GT) interstage extraction gas is proposed to improve the peak regulation performance of the GTCC-based CHP system. The effect of the GT interstage extraction gas method on both the gas turbine expansion ratio and gas turbine extraction gas temperature are studied, and the heat and power operation regions of the GTCC-based CHP system are obtained. Finally, using a heating characteristic day as an example, the peak regulation performance and natural gas consumption changes of the GTCC-based CHP system are analysed. The results indicate that the GT interstage extraction gas method helps to expand the heat and power operation regions of the GTCC-based CHP system under the same output power. During the entire heating season from Nov.15th to Mar.15th, under the GT interstage extraction gas method, the integration of renewable energy is increased by 72071 MW, the natural gas consumption is decreased by 861.74 × 104 m3 and the profit is decreased by $4.72 × 105.

Particle Image Velocimetry (PIV) Investigation of Blade and Purge Flow Impacts on Inter-Stage Flow Field in a Research Turbine

Flow field in the inter-stage is of great importance to jet engine turbine performance and efficiency. Investigation of flow fields is limited by the complex geometrical structure. Traditional measurement techniques, such as hot wire, pressure probe and laser Doppler velocimetry (LDV) can hardly obtain a planar information of the flow field simultaneously. To overcome this difficulty, an instantaneous planar velocimetry technique, the particle image velocimetry (PIV) technique is widely employed. However, there is no publication that studied the detailed flow field by PIV in a turbine inter-stage with the consideration of the influence of rotor blade and purge flow. This paper presents a quasi-three dimensional perspective of flow field between inlet guide vane (IGV) and rotor blade in a research turbine inter-stage by using a 2D PIV system. Coherent structures in the flow field are extracted by the proper orthogonal decomposition (POD) method. Time-averaged results show the ellipsoid structures caused by secondary flow in the inter-stage. Rotor blade influence to axial and radial flow is evaluated by time-averaged data and the first order POD mode. Egress of purge flow (9.4% of main annulus flow rate) leads to a domain with 60% axial velocity loss near hub and a growth over three times in radial velocity. POD analysis of purge flow shows detailed flow migration in the whole measurement plane.

Numerical Simulation of an Ultra-compact Interstage Turbine Burner with Increasing Number of Cavities in the Cavity

The Interstage Turbine Burner (ITB) engine provide significantly higher specific thrust with no or only small increases in thrust specific fuel consumption substitute for conventional gas engine with after-burners. Continue combustion between a high pressure turbine stage and low pressure turbine stage is organized. Ultra-Compact Combustor (UCC), which is one of mainstream design concepts of ITB, has a broad application prospect in the field of aviation with the advantages of compact structure and high combustion efficiency. In order to improve the application of Ultra-Compact Turbine interstage combustor in aero-engine, the numerical simulation was carried out by using CFD technique to research on the influence of the number of cavities in the cavity on the ITB. The results show that the increasing number of structures of cavities in the cavity will enhance the circumferential cavity of the fuel and air mixing and burning, promote the combustion mixture to the mainstream radial transport capacity and improve combustion efficiency and uniformity of exit temperature field.

Test Results for Rotordynamic Coefficients of the SSME HPOTP Turbine Interstage Seal With Two Swirl Brakes

Test results are presented for the HPOTP Turbine Interstage Seal with both the current and an alternate, aerodynamically designed, swirl brake. Tests were conducted at speeds out to 16,000 rpm, supply pressures up to 18.3 bars, and the following three inlet-tangential-velocity conditions: (a) no preswirl, (b) intermediate preswirl in the direction of rotation, and (c) high preswirl in the direction of rotation. The back pressure can be controlled independently and was varied to yield the following four pressure ratios: 0.4, 0.45, 0.56, and 0.67. The central and simplest conclusion to be obtained from the test series is that the alternate swirl brake consistently outperforms the current swirl brake in terms of stability performance. The alternate swirl-brake’s whirl-frequency ratio was generally about one half or less than corresponding values for the current design. In many cases, the alternate design yielded negative whirl-frequency-ratio values in comparison to positive values for the current design. The alternate design can be directly substituted into the space currently occupied by the current design. There is no change in leakage performance.