Woburn, MA, United States
Woburn, MA, United States
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Patent
Concepts Nrec | Date: 2016-04-29

Turbomachines having one or more flow guiding features designed to increase the performance of the turbomachine (3400, 3700, 4000, 4800). In some examples, flow guiding features are designed and configured to bias a circumferential pressure distribution at a diffuser inlet (2210, 2310, 3410, 4204, 4810, 5208, 808) toward circumferential uniformity, otherwise account for such low-frequency spatial pressure variations, increase the controllability of spatial flow field variations, or modifying flow field variations, etc. In some examples, a diffuser (1000, 1100, 1200, 1300, 1500, 1600, 1700, 1800, 1900, 2000, 2100, 2200, 2300, 2400, 2500, 2600, 2700, 2800, 2900, 3000, 3200, 3300, 3404, 4004, 4700, 4804, 5000, 5200, 602, 800, 900) having a row (802) of vanes (2102, 5218, 802) that include a plurality of first vanes (1002, 1102, 1202, 1302, 1402, 1502, 1602, 1702, 1802, 1902, 2002, 2204, 2304, 2402, 2502, 2602, 2702, 2802, 2902, 3002, 3102, 3202, 3302, 812, 902) and at least one second vane (1004, 1104, 1204, 1304, 1404, 1504, 1604A, 1604B, 2206, 2306, 2404, 2504, 2604, 2704, 2804, 2904A, 2904B, 814, 908) having a different characteristic than the first vanes (1002, 1102, 1202, 1302, 1402, 1502, 1602, 1702, 1802, 1902, 2002, 2204, 2304, 2402, 2502, 2602, 2702, 2802, 2902, 3002, 3102, 3202, 3302, 812, 902) are disclosed. In some examples, diffusers (1100, 1900, 2400, 2500) having an aperiodic section (2412, 2512, 2612, 2712, 2812) including one or more biased passages (1006, 1106, 1206, 1306, 1506A, 1606A, 1606B, 2406, 2506, 2606, 2706, 2806A, 2906A, 3206, 4510, 816) for biasing a flow field are disclosed. And in some examples, turbomachines having flowwise elongate recesses (4706) in one or both of a hub (3407, 4002, 4504, 4807, 5002, 5204, 804, 904) and shroud (3406, 4502, 4708, 4712, 4806, 5004, 5202, 806, 906) surface are disclosed.


Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels (602), ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud (514) and hub side of a machine (500) to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine (500). The inventions is dedicated to a casing treatment for turbomachinery.


Systems and methods for reducing the pressure of a first pressurized fluid, thereby reducing the temperature of the pressurized fluid, and utilization of the reduced-pressure and temperature fluid to cool a second fluid. Such an approach can enable a reduction in the size and weight of a hydraulic system, utilize waste energy in a system, and/or minimize electrical power requirements of a system, among other benefits.


Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in regions extending between the adjacent bladed elements, described herein as coupling avoidance zones, where conventional turbomachine design would suggest no structure should be added. In yet other embodiments, CCFGs are located upstream and/or downstream of rows of blades coupled to the bladed elements, including overlapping one of more of the rows of blades, to improve flow coupling and machine performance. Methods of designing turbomachines to incorporate CCFGs are also provided.


Grant
Agency: Department of Energy | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 149.95K | Year: 2016

Supercritical CO2 cycles have the potential to significantly improve efficiency and reduce emissions in power generation. However, the unique fluid dynamic properties of supercritical CO2 that enable these higher efficiencies also complicate the design and layout of the system, particularly its turbomachinery components. The problem stems specifically from the highly non-linear properties of CO2, which pose significant difficulties in modeling. Commercial software companies have been slow to respond to this issue, resulting in a critical unmet market need. The objective of this Phase I effort is to create a comprehensive set of computational software tools that can accurately predict the performance of compressors, pumps and turbines when operating with supercritical CO2. To reduce the scope and complexity of this effort, the specific developments needed for supercritical CO2 will be built on a foundation of existing software tool sets, already developed for turbomachinery design. Once these models have been comprehensively upgraded for the specific demands required, a complete and fully functional system for the confident design of turbomachinery components for supercritical CO2 applications will be realized. Phase I tasks include: The improvement of thermodynamic calculations for the unique demands of supercritical CO2 and its efficient application in computational fluid dynamic analysis. A comprehensive study of how to stabilize the solution process in the existing solver, with recommendations for schematic changes required in Phase II. Development of recommendations to improve turbulence models for non-linear fluid properties, such as supercritical CO2. Development of post-processing functions that can determine the need for nucleation modeling and solution reliability. Recommendations for a suitable nucleation model based on the initial results from Phase I. If this project is carried over into Phase II or Phase III, the commercial applications are extensive. The software would be applicable to many different supercritical CO2 power cycle scenarios, and it will encourage energy saving in other areas where efficient turbomachinery design with real fluid thermodynamic properties is required. Key Words: supercritical, CO2, compressor, power


Grant
Agency: Department of Energy | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 149.95K | Year: 2016

According to a 2014 study commissioned by the Department of Energy, hydropower from more than 3 million untapped streams in the United States could potentially generate 65 gigawatts of electricity and help to reduce greenhouse emissions and pollution. However, the development of hydropower has been limited by several obstacles, as described by the United States Geological Survey: most of the prime locations have already been developed, and the cost, time, and environmental impact of constructing conventional hydroelectric facilities at relatively low power levels are untenable. A low-cost, low- impact, high-performance hydropower turbine is needed to cost-effectively tap into the large amount of this available hydropower. The proposed work will create a low-cost, modular, and very low-head hydroelectric turbine generator unit. This unit will have a small footprint and a reduced environmental impact, and will function in a broad range of operating conditions. By focusing on very low-head applications, many of the issues of free-stream power generation can be avoided while still keeping the site impact and footprint low. Several design technologies (hydrodynamic and structural) can be applied to a small, very low-head hydro turbine to address issues of cost, durability, installation, and performance. Phase I tasks include: • Conducting a study to determine optimum turbine sizing to best utilize the modular stackable nature of the design and accommodate a broad range of installation parameters. • Carrying out a hydrodynamic design study to develop and optimize the axial turbine geometry for low-head applications—including the ability to scale or to stack units to cover a range of flows and heads. • Creating a mechanical design of the turbine generator system, and working to realize the mechanical design benefits described above by incorporating novel drive techniques. • Developing a production cost model for the turbine generator unit that factors in the impact of low-cost manufacturing techniques. If this project is carried over into Phase II or Phase III, the commercial applications are extensive. There are a very large number of existing sites inside and outside the United States where this technology can be applied immediately. Key Words: Hydro, hydro turbine, hydroelectric


Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels, ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud and hub side of a machine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.


Methods, systems, and devices for designing and manufacturing flank millable components. In one embodiment, devices, systems, and methods for designing a flank millable component are provided, in which a user is notified when a component geometry option is selected that will result in the component not being flank millable. In another embodiment, the user is prevented from selecting a geometry option that would result in the component not being flank millable. In yet another embodiment, devices, systems, and methods are provided for manufacturing a component with a flank milling process, in which optimized machine instructions are determined that minimize milling machine motion.


Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in regions extending between the adjacent bladed elements, described herein as coupling avoidance zones, where conventional turbomachine design would suggest no structure should be added. In yet other embodiments, CCFGs are located upstream and/or downstream of rows of blades coupled to the bladed elements, including overlapping one of more of the rows of blades, to improve flow coupling and machine performance. Methods of designing turbomachines to incorporate CCFGs are also provided.


Hydrogen gas compression systems that each include a multistage centrifugal compressor in which each stage has an inlet-to-outlet pressure rise ratio of about 1.20 or greater. In one embodiment, the multistage compressor includes six high-speed centrifugal compressors driven at a speed of about 60,000 rpm. The compressor has an output of more than 200,000 kg/day at a pressure of more than 1,000 psig. The compressors for the compression stages are distributed on both sides of a common gearbox, which has gearing that allows axial thrusts from the compressors to be handled effectively. Each stages compressor has a unique impeller, which is secured to a support shaft using a tension-rod-based attachment system. In another embodiment, the multistage compressor is driven by a combustion turbine and one or more intercoolers are provided between compression stages. Each intercooler is cooled by coolant from an absorption chiller utilizing exhaust gas from the combustion turbine.

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