Part of the DoW SBIR/STTR FY27 Release 2 topic list. Browse all 83 topics by industry or service.
Topic DON27BZ02-NV023 from the DoW SBIR 2027 BAA, Release 2. Pre-release now; proposals due January 6, 2027, 12:00 PM ET.
Quick answer
DON27BZ02-NV023 is a Department of the Navy SBIR topic seeking a low-cost, limited-life gas turbine engine producing 150-300 lbf of sea-level static thrust with a 10-15 hour life for attritable UAS, loitering munitions, and stand-off weapons. It follows a standard Phase I feasibility, Phase II prototype engine structure. Proposals are due January 6, 2027, 12:00 PM ET.
Solicitation at a glance
- Topic number: DON27BZ02-NV023
- Official title: Attritable Turbine for Low-Cost Attack Systems (ATLAS)
- Agency: Department of the Navy
- Program: SBIR (DoW SBIR 2027 BAA, Release 2)
- Award type: Phase I (see topic text for Phase II)
- Award amount: Phase I base up to $200,000 plus an option up to $115,000. Source: Navy Release 2 instructions in DSIP.
- CMMC level: Level 2 (Self)
- ITAR: Yes. Export-controlled (ITAR/EAR); see topic text
- Technology areas: None
- Pre-release (direct TPOC contact allowed): November 4 to December 2, 2026, 8:00 AM ET
- Opens in DSIP: December 2, 2026, 8:00 AM ET
- Proposals due: January 6, 2027, 12:00 PM ET
- Official source: DSIP Topics app (search DON27BZ02-NV023)
BW&CO's take
What the Department of the Navy wants
Small turbofan and turbojet engines in the 150-300 lbf class cost too much and take too long to build for weapons used in mass. The Navy wants a turbofan designed for low unit cost and fast scaling, using additive manufacturing to cut part count, automotive and other non-aerospace production capacity, short-life components, and cheaper materials. Notional targets include SFC under 1.5, 500-1500 W electrical generation, 20k ft cruise, approximately 10 in or less diameter, 25-35 lbm dry weight, air impingement start, and 6-12 months maritime storage. Phase I delivers a design, cost comparison, and component or rig testing. Phase II builds and tests full engines through an endurance run.
Who is a good fit
- Small gas turbine design and testing experience, ideally in the 150-300 lbf thrust class
- Metal additive manufacturing for turbomachinery parts, such as powder bed fusion or DMLS
- Relationships with automotive or other non-aerospace manufacturers for low-cost casting and production
- Component rig testing capability and cost modeling against traditional manufacturing baselines
Watch-outs
- The topic metadata marks it as ITAR-restricted, so plan for export-control compliance, including limits on foreign national participation.
- Phase I expects a proof-of-concept demonstration or test campaign at component rig or lab level, plus CFD, structural, thermal, and cycle modeling.
- Phase II requires physical engines built with low-cost suppliers, a start system, engine controls, environmental testing, and a full endurance run to the mission profile.
- The topic metadata lists CMMC Level 2 (Self). The engine must run on Navy relevant fuels, function after 6-12 months of maritime storage, and meet minimum performance after shore-based and shipborne launch environments (notional launch methods: rail, catapult, or rocket assist).
Think your company fits DON27BZ02-NV023? Talk with BW&CO before the January 6 deadline.
Plan Your DON27BZ02-NV023 Submission
Official topic text (verbatim from DSIP)
The text in this section is copied word for word from the official DSIP topic as published on November 4, 2026. DSIP is the official source and topics can be amended. Always confirm the current version at dodsbirsttr.mil before you submit. Our commentary above is BW&CO's interpretation, not Government guidance.
Title
Attritable Turbine for Low-Cost Attack Systems (ATLAS)
Objective
Design, develop, and prototype a low-cost, limited-life gas turbine engine producing 150-300 lbf of SLS thrust with an estimated engine life expectancy of 10-15 hours, leveraging advanced design and manufacturing techniques to significantly reduce part count, production lead time and scaling, and overall unit cost compared to traditionally manufactured engines in the same class.
Description
The Department of War has an increasing need for affordable, reliable, and rapidly producible propulsion systems to support the proliferation of attritable Unmanned Aerial Systems (UAS), loitering munitions, and stand-off strike weapons. Current small turbofan and turbojet engines in the 150-300 pounds of thrust (lbf) class often rely on traditional aerospace material and manufacturing processes, resulting in high unit costs and long supply chain lead times. These factors are prohibitive for systems intended to be employed in mass or as expendable assets.
This SBIR topic seeks innovative engineering and manufacturing approaches to design a turbofan engine that meets the thrust requirements while dramatically lowering cost per unit. Proposers should consider advanced design and manufacturing techniques to produce a low-cost engine that can leverage existing industrial base capacity to reduce risk to procurement supply chains.
Key technologies and design features to consider are:
- Additive Manufacturing: Utilizing Powder Bed Fusion, Directed Energy Deposition and Direct Metal Laser Sintering (DMLS) to consolidate part count and simplify construction.
- Industrial (Non-Aerospace) Production Capacity: Leverage non-traditional aerospace manufacturing firms to reduce cost. Consider leveraging materials, casting and production techniques found in the automotive sector. Demonstrate a manufacturing pathway that enables rapid scaling and reduces supply chain bottlenecks.
- Short Life/Expendable Components: Utilizing non-traditional lubrication systems, bearings and electronic sub-components to limit cost.
- Optimized Materials: Utilize cost-effective materials suited for limited-life/single-use engine operations rather than traditional high-lifecycle aviation materials, where appropriate.
Performance metrics of interest include specific fuel consumption (SFC), thrust-to-weight ratio, and operational reliability for mission durations typical of attritable UAS or cruise munitions.
The engine will be fully operational utilizing Navy relevant fuels and demonstrate resilience to harsh maritime storage and launch conditions without significant performance degradation. The engine is expected to demonstrate functionality when subject to storage life of 6-12 months in Maritime environments and meet minimum required performance after exposure to shore-based and shipborne launch environments.
Notional performance objectives for this SBIR topic are provided in the Tables below:
Table 1: ATLAS engine notional operational envelop and performance objectives.
Parameter Specification
Electrical Power Generation [W] 500-1500
Thrust, SLS [lbf] 150-300
SFC [lbm/lbf/hr] < 1.5
Cruise Altitude [ft] 20k
Table 2: ATLAS engine notional mass and dimensional properties objectives.
Parameter Specification
Approximate OML Diameter [in] < =10
Weight, Dry [lbm] 25-35
Length [in.] 14-24
Table 3: ATLAS engine notional storage & launch conditions.
Parameter Specification
Start Altitude Sea Level
Start Method Air Impingement
Storage Duration (Wooden Round) 6-12 months, Maritime Environment
Launch & Assist Method Rail, Catapult, or Rocket Assist
Phase I
Conduct a feasibility study and develop a conceptual design for a 150-300 lbf. turbofan engine.
- Identify the specific advanced design and manufacturing techniques to be utilized, optimizing the finished product for cost and producibility.
- Provide preliminary conceptual design modeling and simulation data (e.g., computational fluid dynamics, structural, and thermal analysis, cycle model) to validate conceptual design.
- Develop a comparative cost analysis demonstrating the projected unit cost and production time reductions versus traditional manufacturing baselines.
- Conduct a proof-of-concept demonstration and/or test campaign of the conceptual design, components, materials and manufacturing methods utilizing component level rig testing or lab testing where applicable.
- Monitor ongoing program risk and provide status updates throughout program progression.
- Deliver a Phase II development and testing plan.
Phase II
Refine the conceptual design based on Government feedback and develop a detailed design for a fully functional prototype engine. Transition the Phase I conceptual design into fully functioning, physical hardware and demonstrate engine operation.
- Perform detailed component and system design based on Phase I deliverables.
- Manufacture detailed design test articles (produce physical engines) utilizing low-cost supply chain suppliers.
- Build and assemble fully functioning engine test articles.
- Demonstrate a cost-effective, reliable engine start system.
- Design and integrate a cost-effective engine control solution.
- Conduct a comprehensive test and validation program including completion of the required environmental tests to demonstrate engine performance, reliability and robustness of design.
- Perform a full endurance run to operational mission profile documenting performance.
- Refine mass production cost estimates including complete cost analysis and future cost projections.
- Identify manufacturing industrial base supply chain performers.
- Monitor ongoing program risk and provide status updates throughout program progression. Prepare a Phase III commercialization/transition plan.
Phase III Dual Use Applications
- Utilize lessons learned in the Phase II outcome to perform final detailed design and design for manufacture updates to increase Manufacturing Readiness Level (MRL).
- Update and continue test campaign for finalized engine design qualification/acceptance testing.
- Deliver a comprehensive engine performance test report summarizing performance against Navy-approved ATLAS criteria.
- Provide a detailed transition plan moving from Proof of Concept (POC) to Full Rate Production (FRP),
- Monitor ongoing program risk and provide status updates throughout program progression.
- Interface with airframe producer integrate engine into a host airframe for flight testing.
References
“ONR SBIR Topic N251-056 (2025) Compact Prime Power Source for Unmanned Aerial Systems.” https://navysbir.us/n25_1/N251-056.htm
Brendlinger, K. R., Grannan, N. D., Holley, A. T. and Muraleetharan, K. “Power Output of Small Gas-Turbine Engines.” AIAA SCITECH 2022 Forum, 0063. American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2022-0063
Cukurel, B., et al. “3D Printed Jet Engines, a Micro Gas Turbine Revolution, and the Future of Energy.” Technion, July 2, 2023. https://technionuk.org/news-post/prof-beni-cukurel-3d-printed-jet-engines-a-micro-gas-turbine-revolution-and-the-future-of-energy
Jones, A. D. and Harris, M. M. “An Overview of a Micro-Scale Gas Turbine Combustor Test Campaign.” AIAA SCITECH 2026 Forum, 1566. American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2026-1566
Keywords
Small Gas Turbine Engine, Advanced Manufacturing, Additive Manufacturing, Attritable, Disposable, Expendable Unmanned Arial Systems Propulsion, Low-Cost, 150-300 pounds of thrust, lbf, Limited Life Propulsion
Frequently asked questions
What is DON27BZ02-NV023?
It is a Department of the Navy SBIR topic to design, develop, and prototype a low-cost, limited-life gas turbine engine producing 150-300 lbf of SLS thrust with an estimated life of 10-15 hours, using advanced design and manufacturing to cut part count, lead time, and unit cost.
When is DON27BZ02-NV023 due?
Proposals are due January 6, 2027, 12:00 PM ET. DSIP pre-release began November 4, 2026, and direct contact with the topic authors is allowed only until the topic opens on December 2, 2026, 8:00 AM ET.
Is this a Phase I or Direct-to-Phase II topic?
The topic describes a standard Phase I feasibility study and conceptual design with proof-of-concept testing, followed by Phase II detailed design, fabrication, and testing of full engines. It does not state that it is Direct-to-Phase II.
What are the notional size and performance targets?
Thrust of 150-300 lbf SLS, SFC under 1.5 lbm/lbf/hr, 500-1500 W electrical power generation, 20k ft cruise altitude, outer diameter of 10 in or less, 25-35 lbm dry weight, and 14-24 in length.