AWARD
A -- TURBINE-BASED COMBINED-CYCLE LOW MACH RISK REDUCTION DIRECT CONNECT COMBUSTORTESTING
- Notice Date
- 12/23/2014
- Notice Type
- Award Notice
- NAICS
- 541712
— Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
- Contracting Office
- NASA/Glenn Research Center, 21000 Brookpark Road, Cleveland, OH 44135
- ZIP Code
- 44135
- Solicitation Number
- NNC15TA07T
- Archive Date
- 1/14/2015
- Point of Contact
- Melissa A Merrill, Contract Specialist, Phone 216-433-6359, Fax 216-433-5489, Email Melissa.A.Merrill@nasa.gov
- E-Mail Address
-
Melissa A Merrill
(Melissa.A.Merrill@nasa.gov)
- Small Business Set-Aside
- N/A
- Award Number
- NNC15TA07T
- Award Date
- 12/15/2014
- Awardee
- Aerojet Rocketdyne HWY 50 & Aerojet Rd Rancho Cordova, CA 95670-6000
- Award Amount
- 1099916
- Description
- BACKGROUND One of the major challenges to achieving effective and affordable hypersonic flight is the ability to have a single engine start at zero velocity and accelerate to Mach 6+. To date the combined cycle engine approach, where one engine known as a gas turbine accelerates to a velocity that enables another engine known as a scramjet to take-over and accelerate the rest of the way has been investigated. This would be an acceptable solution except that the take-over velocity for the scramjet has been too high to be able to use an Off-the-Shelf (OTS) turbine as the first engine. Therefore getting to hypersonic speeds has been held back because of the need for two costly engine developments with uncertain outcomes on the success of both engine developments. Aerojet Rocketdyne (AR) has developed technology which has shown through testing, under Independent Research and Development (IRAD) funding (using the direct connect combustor internal mold lines from DARPAs Falcon Combined Cycle Engine Test, FaCET, program), that it may very well be possible to have a dual mode ramjet propulsion system that allows the take-over velocity to be reduced to Mach 2 or lower and transitions to the scramjet engine permitting the vehicle to accelerate to cruise operating conditions. This take-over velocity would allow an OTS available turbine engine to be used, greatly reducing cost and risk and decreasing the development time by at least 10 years. The purpose of this task is to use the scramjet technology developed by AR and explore and characterize ignition, operability and performance at simulated conditions representing Combined Cycle and Ramjet modes of operation over the mode transition corridor. SCOPE OF WORK The overall objective of the proposed Turbine-Based Combined-Cycle (TBCC) Low Mach Risk Reduction Direct Connect Combustor (DCC) Testing is to advance key enabling technology for TBCC hypersonic propulsion systems by extending low Mach and altitude operation of ARs 3rd generation powerhead for the dual-mode scramjet propulsion system while maintaining maximum flight Mach capability. The specific objectives are to explore and characterize ignition, operability and performance at simulated conditions representing Combined Cycle and Ramjet modes of operation over the mode transition corridor. AR will conduct a hydrocarbon fueled direct connect test that provides a flexible, low cost approach which will reduce risk for TBCC hypersonic propulsion systems. The contractor shall perform the following Tasks: (1) task planning and status, (2) integrated and coordinated pre-test analyses, (3) hardware refurbishment and fabrication, (4) ground tests in a jet burner test stand, and (5) post-test data analysis and reporting to meet program objectives.
- Web Link
-
FBO.gov Permalink
(https://www.fbo.gov/spg/NASA/GRC/OPDC20220/Awards/NNC15TA07T.html)
- Record
- SN03603689-W 20141225/141223234738-5bb1e5634566b55e7ee94effeb1253f0 (fbodaily.com)
- Source
-
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