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6 CONCLUSIONS The initial results obtained from the small scale Brayton cycle loop developed under this LDRD have provided the first experimental data on compression near the critical point of CO2. Stable operation of the compression stage in this region of non-linear working fluid properties was a critical issue for establishing the viability of this cycle, The results obtained in this project demonstrated stable and controllable operation near the critical point over a range of conditions and confirmed the performance potential of these cycles. The small scale loop used modular and reconfigurable hardware to allow the flexibility to construct a range of compression and Brayton cycle configurations, and also to serve as a test bed for the development of the key bearing, seal, and controller technology necessary for loop operations. . The key component of these loops is the turbo-alternator-compressor unit and the technologies used in its design. In its final configuration, the TAC uses gas foil bearings, a high speed permanent magnet motor/alternator and labyrinth gas seals to reduce the rotor cavity pressure. Because of the extremely high power densities and fluid density, Sandia has filed a Technical Advance for the TAC design. The early tests are focused on measuring leakage flow rates, windage losses, balancing thrust loads and measuring the compressor performance characteristics. Many of these early tests used ball bearings (with limited life) rather than gas foil bearings to allow for early testing and to minimize gas foil bearing development risks. The results of these tests were discussed in this report. The compression loop has been operating for over a year. Nearly 100 test operations have been performed on the loop including measurements of the compressor performance map, the thrust loads (with just a compressor or with a small turbine), labyrinth seal leakage tests, operations in the two-phase region, and operations using gas foil bearings. The loop has been operated up to speeds of 65,000 rpm and at flow rates of 4 lb/s and at a pressure ratio of 1.65. Future testing will focus on measuring the performance maps for different compressor inlet conditions but still near the critical point. Other tests will explore surge conditions. Testing will also be performed with gas-foil bearings and various types of seals to determine the compatibility of these seals with gas-foil bearings and to estimate or determine seal leakage flow rates. In general, the measured data from the supercritical CO2 compression loop agree with our models. However, we are still early in the test program and more data needs to be measured over a wide range of conditions. Although these are only the first results to be analyzed, these results indicate that the basic design and performance predictions are sound. For example, we believe that the measured compression loop efficiency maps validate the “similarity” approach used to predict the performance curves and to design the compressors and turbines. The compression test loop is now the test bed that has largely confirmed the parameters to support the next stage of development, which is a 1 MW heater-class split- flow re-compressor Brayton cycle that will be capable of generating up to 250 kWe. 91PDF Image | Operation and Analysis of a Supercritical CO2 Brayton Cycle
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