Company
Portfolio Data
Back to Company SearchConcepts NREC, LLC
UEI: PKMJNWK4V2U1
Number of Employees: 102
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
SBIR/STTR Involvement
Year of first award: 1987
51
Phase I Awards
20
Phase II Awards
39.22%
Conversion Rate
$4,992,235
Phase I Dollars
$15,624,109
Phase II Dollars
$20,616,344
Total Awarded
Awards
Integrated Cooling and Secondary Flow Design System
Amount: $1,244,301 Topic: AFX244-DPCSO1
Gas Turbines (GTs) for piloted aircraft and drones are among the most complicated components in a flight program, and the most challenging part of a system to design. The state-of-the-art is such that while current tools can design turbomachinery primary flow paths expeditiously and accurately, incorporating secondary flow systems and cooling schemes lead to long design and development cycle times. This SBIR effort will mean the introduction of state-of-the art methods for the design, layout, and analysis of turbomachinery secondary flows. Concepts NREC has a pre-existing fundamental design system that has many of the needed modifications/additions in place; what is missing is an appropriate integration of the disparate elements In addition to the development of SFS flow path geometry generation utility with 1D network solver capability, we intend to link new and successful existing solvers together into a comprehensive design system, taking full account of secondary flow effects. The mature state of the already-existing component products will provide a strong foundation and minimize the risk involved in a straight to Phase II program. á
Tagged as:
SBIR
Phase II
2024
DOD
USAF
Cost-Effective RBC for High-Power X-Ray Applications
Amount: $199,294 Topic: C57-07a
The DOE is in need of affordable and robust cryogenic cooling solutions for use in high-power optics applications. These cryogenic cooling solutions must remain cost effective, exhibit high operational stability, and be adaptable for current and future needs. Specifically, in support of the DOEĺs high-brightness light sources utilizing silicon mirrors and crystals, a cryogenic cooling solution is required to provide the necessary heat lift of 250+ W in the region of siliconĺs zero crossing of its thermal expansion coefficient, at approximately 125 K. Beyond the DOE, the worldwide market for industrial and commercial cryocoolers is developing based on a need for High-Temperature Superconducting (HTS) cooling needs. For example, superconducting motors for wind turbines are being pursued in Europe. As the world economy continues to grow and HTS applications become more widespread, these industries will have an increased need for cryocoolers to meet a growing need of superconducting applications. Concepts will use Phase I to concentrate on configuration and optimization of the Reverse-Brayton Cryocooler to provide integrated cooling needs. Phase I will be used to explore several fundamental questions through R&D, including defining system specifications, deciding on preferred cycle gas and defining the turbomachinery drivetrain design to be used going into Phase II.
Tagged as:
SBIR
Phase I
2024
DOE
Advanced sCO2 Turbine for Concentrated Solar Power Application
Amount: $199,744 Topic: C58-17b
Supercritical CO2 (sCO2) offers an extremely efficient thermal to electricity conversion. However, this is only at exceptionally high temperatures, which push the boundaries of current turbomachinery component technology, namely the bearings and seals. Previous and current DOE research has either involved smaller scale component technology that does not scale up well to deliver higher power, or involves placeholder component technology to facilitate larger scale demonstrations, postponing the integration of truly successful and reliable turbomachinery component technology. The objective of this project is to design a test rig for demonstrating scale-appropriate bearing and seal component technology that effectively replicates >1MWe power levels. This will be done with an actual turbomachine with actual turbomachine conditions, in an effort to accurately represent the challenges the component technologies will be facing. Phase I will build upon previous magnetic bearing proof of concept work by designing the rest of the turbomachine test rig. Phase II will finalize this design, source the hardware, assemble, and test the rig, in partnership with an sCO2 test facility. Successful implementation of the Phase II plan will provide a) preliminary test data for magnetic bearings and the selected seal in a medium-power sCO2 environment, and b) provide a vendor and technology agnostic accessible test rig for future component technology benchmarking and comparison for the benefit of the industry, helping enable ôat-scaleö sCO2 power cycles.
Tagged as:
SBIR
Phase I
2024
DOE
Space Exploration Hydrogen Boost Pump
Amount: $149,994 Topic: Z10
Concepts NREC proposes an electrically driven, boost pump, with an integrated motor to deliver liquid hydrogen saturated at 20 psia, at an increase in pressure of between 25 and 45 psid, and a flow rate of at least 0.6 kg/s. The target life will be 7500 hours with 3000 start/stop cycles. The boost pump can be used in conjunction with a high-pressure ratio pump for a variety of space exploration missions of interest to NASA. Because of differences in density, the hydrogen boost pump can be used for other fluids, such as LOX and methane, and satisfy are good portion of the flow and pressure rise needs for these propellants in launch and in-space applications. The pump will be designed with the intent to operate with other fluids to maximize its usefulness. The hydrogen pump development will enable more rapid development of other motor driven aerospace pumps for a variety of propellants and purposes for lower long term development costs.
Tagged as:
SBIR
Phase I
2024
NASA
Integrated Brayton Cryocooler for LOx and LH2 Applications
Amount: $749,482 Topic: Z10
NASA is in need of affordable and robust cryogenic cooling solutions for use in space applications.nbsp; In support of the Artemis program, NASA seeks innovative integrated refrigeration cycles for use in liquefaction of hydrogen and oxygen from the lunar surface. Based on initial estimates from Phase I activities, 330+ W of cooling is needed at 90 K and 130+ W of cooling is needed at 20 K to support at least 11.7 metric tons per year.nbsp; Currently, space-based cryocoolers have yet to demonstrate cooling beyond 20 W at 20. Concepts NREC (CN) is working towards the demonstration of two high-capacity helium-based reverse-Brayton cryocoolers, and plans to leverage these cryocoolers to develop a novel integrated two-stage helium system capable of supporting both oxygen and hydrogen liquefaction needs on the Moon. The proposed solution will increase the current state-of-the-art in cryogenic cooling by an order of magnitude. The two lowest TRL/MRL components derived from Phase I activities are a micro-tube recuperator with a titanium construction replacing the legacy materials, and a compressor capable of operation under lunar surface ambient conditions. The titanium micro-tube recuperators utilize a proven, underlying design; the same manufacturing method and models can easily be adapted to the changes brought upon by the change to titanium, and development risk is considered low. Lunar ambient compressor operation has the highest system risk when looking at the changes from legacy CN demonstrations. Existing turboalternator powertrain technology will be leveraged to develop a compressor powertrain that is capable of operation at the reduced ambient conditions. The capabilities of the newly developed powertrain will need to handle larger thrust loads at higher rotational speeds than what is currently found on the turboalternators. Results from this study will provide valuable input into NASArsquo;s on-going Cryogenic Fluid Management directives.
Tagged as:
SBIR
Phase II
2022
NASA
Integrated Brayton Cryocooler for LOx and LH2 Applications
Amount: $124,594 Topic: Z10
NASA is in need of affordable and robust cryogenic cooling solutions for use in space applications.nbsp; Specifically, in support of its Artemis program, NASA seeks innovative integrated refrigeration cycles for a combination of hydrogen and oxygen liquefaction on the lunar surface (topic Z10.01). Based on initial estimates, nominally 300 W of cooling is needed at 90 K and 20 K to support at least 11.7 metric tons per year (3.3 kg/hr of oxygen and 0.4 kg/hr of hydrogen). Currently, Concepts NREC (CN) is working towards the demonstration of a high-capacity reverse-Brayton cryocooler based on the needs of several high-temperature superconducting and liquefaction applications. On the proposed NASA Phase I project, CN proposes to leverage its high-capacity Brayton cryocooler development effort by pursuing a novel integrated system capable of supporting oxygen and hydrogen liquefaction needs on the Moon. Beyond providing an integrated solution, the proposed system will dramatically increase the current state-of-the-art in space-based cryogenic cooling capacity. CN proposes to focus its Phase I efforts on cycle and configuration analysis and optimization, consistent with the Z10.01 solicitation expectations. In collaboration with NASA personnel, CN will select the optimum configuration for maturation in Phase II. During Phase II, the lowest Technical Readiness Level (TRL) component will be selected for further development.
Tagged as:
SBIR
Phase I
2021
NASA
Low-Cost, High-Performance Brayton Cryocooler
Amount: $1,499,897 Topic: N181-041
The Navy requires affordable and robust cryogenic cooling solutions for use in High Temperature Superconducting magnet technology. While Stirling refrigerators are commonly used in the cryogenics industry, they do not scale well to large capacities and inherently exhibit significant vibration due to their piston-based operation. Therefore, Concepts NREC (CN) proposes to develop a reverse-Brayton cryocooler. Reverse-Brayton cryocoolers offer several unique advantages, such as high-capacity cooling at high efficiency, and long life without maintenance due to wear-free and vibration-free components. Indeed, reverse-Brayton cryocoolers are inherently high-capacity systems, and rely on turbomachinery with noncontact bearings, resulting in wear-free and vibration-free operation. During Phase II, CN proposes to fabricate the cryocooler components, assemble the cooler and conduct testing aimed at demonstrating Technology Readiness Level 5.
Tagged as:
SBIR
Phase II
2020
DOD
NAVY
Low-Cost, High-Performance Brayton Cryocooler
Amount: $124,962 Topic: N181-041
The Navy requires affordable and robust cryogenic cooling solutions for use in High Temperature Superconducting (HTS) cable technology. Currently, gaseous helium is cooled by a cryocooler through a cryogenic heat exchanger and circulated using a helium circulation fan through a superconducting cable. While Stirling refrigerators are commonly used in the cryogenics industry, they do not scale well to large capacities and inherently exhibit significant vibration due to their piston-based operation. Therefore, Concepts NREC (CN) proposes to develop a reverse-Brayton cryocooler. Reverse-Brayton cryocoolers offer several unique advantages, such as high-capacity cooling at high efficiency, and long life without maintenance due to wear-free and vibration-free components. Indeed, reverse-Brayton cryocoolers are inherently high-capacity systems, and rely on turbomachinery with noncontact bearings, resulting in wear-free and vibration-free operation. During Phase I, CN will complete the design of the cryocooler system, including its key components: the compressor, the turbine and the recuperator. During the Phase I Option, CN will perform risk reduction activities in preparation for Phase II. During Phase II, CN will build and test the cryocooler.
Tagged as:
SBIR
Phase I
2018
DOD
NAVY
Magnetic Bearings for Supercritical CO2 Service
Amount: $999,795 Topic: 29f
The technology development for the supercritical CO2 (sCO2) power plant is well underway, and the first pilot plants are now under construction. The new pilot plants are sized for a 10 MW net power output; a good size to gain valuable data for larger utility scale power plants. This is also a very good size for the smaller, distributed power applications. The distributed power application is envisaged as the primary application for the roll out of the technology. The reliability of the plants during the introductory phase will be very important. A panel of power plant executives at the recent DOE conference on sCO2 has made it clear that the initial cost, operating cost, and up-time reliability must be demonstrated before any significant investment at the public utility level is seen. Pursuant to this point, the reliability of the system will be the next great focus for the sCO2 systems. When a Failure Modes and Effects Analysis (FMEA) is done at a system level, machinery design with fault tolerance will be a priority. Machinery up-time and system contamination effects will be high on the list of risks. The new machines proposed for the pilot plants use oil bearings and gas seals. A turbocompressor with two gas seals and another machine with integral gear and 4 gas seals will be installed in the plants. It is well understood that reliability for turbomachinery is highly dependent upon the bearing and sealing systems. Upsets, surges, fluid-driven instability, start-up variations, and variation in thrust loading are all acceptable if the bearings and seals can tolerate them. Concepts NREC has proposed a design approach to improve reliability by addressing the bearing and seals. This approach includes: 1) Reduce the number of seals down to one seal. 2) Eliminate the oil entirely with magnetic bearings. Elimination of the oil removes a source of seal distress, and also serves to eliminate the possibility of fouling of the heat exchangers. The magnetic bearings will provide improved monitoring capability and can be used for active fluid force measurement in a machine.
Tagged as:
SBIR
Phase II
2018
DOE
A Novel Integrated Low Leakage IPS and Thrust Bearing for Rocket Turbopumps
Amount: $149,952 Topic: AF181-031
A novel integrated inter-propellant seal and thrust bearing (IPS/TB) for rocket turbopump applications that uses the latest technology developments in seal coatings and additive manufacturing to advance the state-of-the-art. The IPS/TB has low propellant loss, requires little or no purge gas, and no continuous purge when the turbopump is not in operation. The thrust bearing portion can handle all the turbopump thrust requirements for an upper-stage or in space propulsion engine in a simple package without the axial stack-up tolerance problems or secondary flow losses associated with other thrust management solutions. The technology is applicable to turbopumps for booster, upper-stage, and in-space propulsion engines and for a variety of propellants including, LOX, LH2, LNG, and RP1.
Tagged as:
SBIR
Phase I
2018
DOD
USAF