SPECIAL NOTICE
A -- ENGINEERING CAPABILITIES FOR AIRBREATHING PROPULSION, APPLIED TO FUTURE SPACE LAUNCH VEHICLES
- Notice Date
- 5/9/2003
- Notice Type
- Special Notice
- Contracting Office
- NASA/Langley Research Center, Mail Stop 144, Industry Assistance Office, Hampton, VA 23681-0001
- ZIP Code
- 23681-0001
- Solicitation Number
- NASA-SNOTE-030509-002
- Archive Date
- 5/9/2004
- Description
- The National Aeronautics and Space Administration's (NASA) Langley Research Center is seeking partners to develop technology proposals in response to the announcement below. Synopsis: The National Aeronautics and Space Administration (NASA) has released a NASA Research Announcement (NRA) on March 24, 2003 soliciting government-led proposals in propulsion research and technology in support of NASA's Next Generation Launch Technology Program (NGLTP). This NRA is being executed in parallel with NRA-03-GRC-PRT-01, soliciting industry-led proposals. Both announcements solicit proposals to advance technologies for airbreathing and combined-cycle propulsion systems in the following categories: rotating seals and components, propulsion flowpath components and engineering capability development. Successful proposals must present topics that advance Technology Readiness Levels (TRL) and address technical performance metrics derived from assessments of candidate reusable launch vehicle (RLV) vision vehicle concepts. Vision vehicle concepts include single-stage-to-orbit (SSTO) vehicles powered by rocket-based combined-cycle (RBCC) and turbine-based combined cycle (TBCC) propulsion systems as well as two-stage to-orbit (TSTO) systems powered by high-Mach gas turbine engines and rocket or RBCC engines. Technical performance metrics are derived from requirements that enable system functionality or provide increased weight and performance margin to reduce the cost and enhance the safety of future RLV systems. The NGLT program will competitively select, through a peer review process, proposals to participate in the program. The total proposed period of performance should not exceed 36 months. NASA Langley Research Center (LaRC) is seeking partners from other government agencies, industry, academia and Federal Funded Research and Development Centers (FFRDC) to participate with NASA LaRC Principal Investigators (PI) in the NGLT program to develop proposals for propulsion research and technology in the area of engineering capability development, as described further in the 5 proposal descriptions given below. Proposal topics may include investigations of ramjet combustion physics, development of advanced test instrumentation for RBCC and TBCC propulsion systems, advanced modeling capabilities, and wide operating range design tools and databases. This partnering opportunity does not guarantee selection for award of any contracts, nor is it to be construed as a commitment by NASA to pay for the information solicited. It is expected that the partner(s) selected would provide (at no cost to NASA) conceptual designs, technical data, proposal input, project schedules and cost estimates consistent with the requirements of the NRA for government led proposals. Potential partners must demonstrate the capabilities and experience to perform research activities consistent with the efforts synopsized for the LaRC proposals. Partners must work collaboratively with NASA and other potential government, industry and academic partners to perform the required tasks. Partner selection(s) will be made by LaRC based on the following criteria in the following order of importance: (1) Relevant experience, past performance, technical capability and availability of key personnel: This criteria evaluates the proposer's relevant recent experience, past performance in similar research activities, technical capability to perform the research, and key personnel available to support the research. Substantive evidence (points of contact and telephone numbers) of successful participation in similar developments should be included. (2) Facilities and capabilities. This criterion evaluates the proposer's facilities and research capabilities (testing and analysis) to conduct the proposed research task. The proposers should discuss facility availability, access, and the ability to meet the proposed objectives. (3) Cost and schedule control. This criteria evaluates the proposer's ability to control both cost and schedule. The proposer should provide evidence of successfully controlling cost and schedule for similar programs or provide evidence of management processes in this area. Responses should be limited to 5 pages (12-point font) and address each of the criteria. All responses should be sent to: NASA Langley Research Center, Attn: Cindy W. Albertson, Mail Stop 168, 12 Langley Boulevard, Hampton, VA 23681. The preferred method of submission is via electronic mail to: c.w.albertson@larc.nasa.gov. The due date for submission is COB May 23, 2003. Technical questions should be addressed to the technical points of contact identified in the proposal synopses given below. Procurement questions should be directed to Mary Jane Yeager, NASA LaRC, Office of Procurement, 757-864-2473. Partners selected under this synopsis will participate in the development of government-led proposals in response to the NRA dated March 24, 2003. The technical requirements and NASA LaRC points of contact for technical questions are provided for each technology proposal: 1. Over/Under Inlet Performance and Integration for TBCC Engines Technical Point of Contact: Dr. Saied Emami, Ph: 757-864-8326, email: s.emami@larc.nasa.gov The objective of this effort is to establish performance relationships between high and low speed inlet configurations for TBCC propulsion systems for future space launch vehicles. Inlet performance and operability will be characterized through wind tunnel experiments of a parametric TBCC inlet configuration. Langley is seeking partners with which to collaborate on TBCC inlet geometry and optimization, based on experimental results. The partner(s) must work collaboratively with government representatives and other potential industry and academic partners to perform this task. 2. Mach 3-5 DMSJ Isolator Operability/Modeling. Technical Point of Contact: Dr. Aaron Auslender, Ph: 757-864-6545, email: a.h.auslender@larc.nasa.gov The technical objective of this task is to obtain ramjet data, both in the started and unstarted modes of engine operation, for the enhancement of isolator performance prediction capabilities and associated inlet design issues. Primarily, this effort will focus on combustor inlet interaction mechanisms utilizing engine configurations applicable to NASA-NGLT missions. Classified hardware and ITAR restricted analysis techniques will be employed to further the TRL of this operational regime. Partnerships are sought having a demonstrated experimental and analytic expertise in this general discipline. The partner(s) must work collaboratively with government representatives and other potential industry and academic partners to perform the tasks described above. 3. Mach 3-5 RBCC and TBCC Combustor Performance and Associated Flow Diagnostics and Analysis Technical Point of Contact: Mr. Diego Capriotti, Ph: 757-864-6200, email: d.p.capriotti@larc.nasa.gov The objectives of this effort are to investigate the use of surrogate gaseous fuels in place of heated JP7 fuel, and to develop scaling parameters to correlate existing hydrogen fuel combustion data with newer JP7 fuel combustion data. A parametric investigation will be conducted in the NASA Langley Direct Connect Supersonic Combustion Test Facility (DCSCTF) using a combustor model at simulated flight enthalpies associated with flight at Mach 3, 4, and 5. The combustor model will be fueled with heated liquid JP7, gaseous hydrogen, and gaseous ethylene. Comparison and analyses of the performance of the combustor with the different fuels at the different test conditions will be conducted. Langley is seeking partners with which to collaborate on the analyses of the acquired experimental data. Analyses could include (1) quasi-one-dimensional engineering analysis, (2) full three-dimensional Computational Fluid Dynamics (CFD) simulation, and (3) any innovative analytic techniques. The partner(s) must work collaboratively with government representatives and other potential industry and academic partners to perform the tasks described above. 4. Flow Diagnostics and Analysis Tool Development for Combined Cycle Engines Technical Point of Contact: Dr. J. Philip Drummond, Ph: 757-864-2298, email: j.p.drummond@larc.nasa.gov The objective of this task is to develop a database for the design of wide operating range propulsion systems and components including combustors and nozzles. The database will be used to develop models for turbulence and combustion to be incorporated into CFD codes used in the design of supersonic/hypersonic engine flow paths. In particular, these CFD codes will be used to design rocket based combined cycle (RBCC) and turbine based combined cycle (TBCC) engine flow paths and individual components for these engine types. This effort will be conducted with the goal of raising the TRL of the turbulence and combustion modeling aspects of the CFD codes. Langley is seeking partners that will collaborate in the development of experiments from which the required database can be produced and in the development of turbulence and chemistry models from the database to be used in CFD design codes. The partner(s) must work collaboratively with government representatives and other potential industry and academic partners to perform the tasks defined above. 5. Combustion Characterization of Catalytically-Cracked Hydrocarbon Scramjet Fuels Technical Point of Contact: Dr. Gerald Pellett, Ph: 757-864-6241, email: g.l.pellett@larc.nasa.gov The objective of this task is to characterize catalytically cracked dual mode scramjet hydrocarbon fuels in terms of speciation and flameholding potential. Part of this task will focus on the development of an ambient-temperature fuel composition that mimics cracked-fuel combustion and can be assessed numerically using available chemical kinetics. Flame holding potential will be characterized using an Opposed Jet Burner (OBJ) system to be developed as part of this effort. Speciation will be determined from grab samples that will be analyzed for major constituents. Langley is seeking partners to analyze the grab samples for major constituents. The partner(s) must work collaboratively with government representatives and other potential industry and academic partners to perform the tasks defined above.
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