SPECIAL NOTICE
A -- Alternate Concept Engine (ACE) Technology Demonstration - TIA Template
- Notice Date
- 2/25/2016
- Notice Type
- Special Notice
- NAICS
- 541712
— Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
- Contracting Office
- Department of the Army, Army Contracting Command, ACC - RSA (W911W6) (AATD) (SPS), LEE BLVD BLDG 401, FORT EUSTIS, Virginia, 23604-5577, United States
- ZIP Code
- 23604-5577
- Solicitation Number
- W911W6-16-R-0006
- Archive Date
- 4/29/2016
- Point of Contact
- Kenneth M. Hood, Phone: 7578780103, Laurie Pierce, Phone: 757-878-2071
- E-Mail Address
-
kenneth.m.hood.civ@mail.mil, laurie.a.pierce2.civ@mail.mil
(kenneth.m.hood.civ@mail.mil, laurie.a.pierce2.civ@mail.mil)
- Small Business Set-Aside
- N/A
- Description
- draft TIA 1.0 PURPOSE AND BACKGROUND Recently, the Department of Defense (DoD) has concluded that the rotary wing aviation fleet is aging and upgrades to current fleet aircraft will not provide the capabilities required for future operations. Significant improvement in vertical lift, range, speed, payload, survivability, and reliability are all required to meet future concept of operations for Army Aviation and can effectively be achieved through the application of new engine architectures and designs. Life cycle costs must also be addressed with emphasis on reducing operational costs and the logistical footprint associated with Army Aviation. Future capability planning groups, such as the Future Vertical Lift (FVL) Working Group (a joint DoD activity led by the Army Aviation Center of Excellence), have developed notional capability needs for next-generation future rotorcraft. The capabilities sought for future rotorcraft include combinations of ambient condition hover, speed, range, fuel efficiencies, and troop/payload capacities significantly beyond any current rotorcraft. Additionally, capabilities have been examined, covering some of the potential major missions currently envisioned for future rotorcraft. These capabilities are looking for significant platform speed and mission range increases compared to current rotorcraft. In short, although specific mission performance requirements envisioned for future rotorcraft are still in development, they are expected to significantly expand the operating envelope relative to the current fleet. Possible scenarios may include operating in hover at sea level to approximately 10,000 ft altitudes in hot/cold climates and cruising at altitudes possibly up to 30,000 ft. Platform speeds in excess of 230 knots are envisioned as part of the future mission sets. With such demanding performance mission set, a robust, adaptive propulsion system design is necessary to meet these versatile, wide operating range requirements. Additionally, significant advancements in engine component/system technologies that enhance performance (horsepower/weight (HP/Wt), specific fuel consumption (SFC)) and life cycle cost (durability, reliability, sustainability) are envisioned to affordably provide the characteristics needed for future rotorcraft platforms and upgrades to current rotorcraft platforms. For future rotorcraft to be able to efficiently meet their aggressive mission profiles, turboshaft engine designs will need a significant technological advancement to provide the needed performance capability. One critical technology need area is in advanced variable speed power turbine design. Current state-of-the-art power turbines operate in the 95-105% speed range, operating to a fixed 100% speed for normal operation. For certain aircraft configurations, future power turbine designs will need to be robust enough to allow for optimized power turbine speed in the range of 55-105%. A robust power turbine design, capable of 55-105% speed operation at high efficiency levels, will provide a versatile power system design compatible with tilt rotor aircraft and rotorcraft with an optimum speed rotor system; these are just some of the configurations being considered for future rotorcraft. Variable speed power turbines may require supporting technology solutions to allow the effective integration with the propulsion system and platform interfaces to fully realize the wide output speed range capability for future rotorcraft platforms. Advancements may be needed in: (1) mechanical systems to handle aeromechanical challenges associated with varying shaft speeds, associated potential mode crossings, and bearing support needs; (2) exhaust system technologies to allow current and future infrared signature suppressors to handle the large swirl angle swings associated with high and low output speed operation; and (3) any other potential technology areas. Call W911W6-16-R-0006, Alternate Concept Engine (ACE) Technology Demonstration, solicits proposals for the development and Technology Readiness Level (TRL) 6 demonstration of turbine engine technologies that provide variable output speed operation, high performance, and improved life cycle cost under the Engines & Drive Trains Research Opportunity of the Master Broad Agency Announcement (BAA) W911W6-16-R-0004 which is posted to Federal Business Opportunities (FedBizOpps) at https://www.fbo.gov. 2.0 RESEARCH OPPORTUNITY DESCRIPTION The objective of this BAA Call is to develop and perform engine-level validation (to TRL 6) of variable speed power turbine technology and any required supporting component technologies to enable this capability. Another objective of this Call is to develop and perform engine-level validation (to TRL 6) of innovative engine components/system technologies that provide significantly enhanced performance and improved life cycle cost at the engine and platform level. TRL 6 is defined as completing component/technology validation in a relevant environment via full engine testing. The ACE program is soliciting component technologies that support propulsion systems in the 2,000-10,000 shp class that could power a range of future rotorcraft sizes from reconnaissance-sized rotorcraft to cargo-sized rotorcraft, as well as support enhancements to currently fielded platforms. The ACE program shall consist of design, fabrication, component rig testing (as appropriate), and engine demonstration testing aimed at achieving the variable speed power turbine goals (stated in detail below) as well as showing improvements in the overall ACE desired characteristics for application to future rotorcraft platforms. ACE program goals, characteristics, and associated notes/ground rules include the following: Variable Speed Power Turbine Goals (required demonstration): •Power turbine output speed range: 55% ≤ NPT ≤ 105% •Cruise at 25,000 ft ISA: Power turbine adiabatic efficiency at Maximum Continuous Power (MCP) rated temperature, 55% NPT: ≥ 90% •Cruise at 15,000 ft ISA: Power turbine adiabatic efficiency at Maximum Continuous Power (MCP) rated temperature, 75% NPT: ≥ 91% •Take-Off/ Hover at Sea Level Standard Day: Power turbine adiabatic efficiency at Maximum Rated Power (MRP) rated temperature, 100% NPT: ≥ 92% •Life: > 6,000 hours life, > 15,000 cycles low cycle fatigue with exception of 7,500 cycles for turbine blades and combustor liners (cycles to crack initiation). See Note 1 and 2. Notes: 1.Life analysis will assume for MCP and below power ratings: a.75% duration at 55% power turbine speed b.25% duration at 100% power turbine speed 2.Lifing Usage Spectrum shall be defined as: Structural Life. The engine and all components will be designed with a minimum life of 6,000 hours using the following usage spectrum: Power Condition % Time Contingency 0.1 Maximum Rated (MRP) 2 Intermediate 7 Maximum Continuous (MCP) 45.9 60 percent MCP 20 40 percent MCP 20 Idle 5 Low Cycle Fatigue (LCF) Life. All parts will be designed for a LCF life of 15,000 cycles (based on crack initiation) or greater with the exception of turbine blades and combustor liners. Turbine blades and combustor liners will be designed for a LCF life of 7,500 cycles or greater based on crack initiation. A single LCF cycle is defined as follows: Approximate Approximate Total Time Schedule Time (Minute) (Minute) Event 0.5 0.5 Start Engine 2.5 2.0 Run at Idle 2.6 0.1 Accelerate to maximum rated power 5.1 2.5 Run at maximum rated power 5.2 0.1 Decelerate to Idle 8.2 3.0 Run at Idle 8.3 0.1 Accelerate to max continuous power 10.8 2.5 Run at maximum continuous 10.9 0.1 Decelerate to Idle 12.9 2.0 Run at Idle 15.0 2.1 Shut down and cool down Notes: Maximum power shall be defined as not less than 105% of IRP. MCP shall be defined as 85% of MRP. Life is based on: minus 3 sigma material properties, and 6,000 ft. 95F operating conditions. Offerors shall demonstrate the proposed variable speed power turbine and enabling technologies to a TRL 6. The proposed demonstration of variable speed capability must include all technologies required to fully demonstrate and enable wide power turbine speed operation. Offerors shall address rotordynamics issues associated with wide power turbine speed operation through their technology design and demonstration approach. Engine demonstration vehicle size shall be in the 2,000 - 10,000 shp size class. In an effort to maximize component demonstration capability for the ACE program, it is encouraged to utilize existing engine assets to demonstrate ACE technologies to a TRL 6. However, demonstration on advanced propulsion system assets (technology demonstrator assets) will be preferred over TRL 6 demonstration using existing, fielded engine assets. Demonstration on more advanced test vehicles will validate the technologies in an environment that is more relevant to that of advanced engines that will be used in future rotorcraft. Desired ACE Characteristics (for additional component demonstration(s)): •Specific Fuel Consumption (SFC) Across the Envelope: Consider technologies that address reduction of SFC across a wide range of operating conditions. This includes consideration of conditions that encompass the variable speed power turbine goals (0 - 25,000 ft altitude, 55-105% power turbine speed) as well as operation in high hot, high cold hover and cruise conditions. •Horsepower to Weight Ratio (HP/Wt): Consider the implications of weight for given technologies and how they impact the overall HP/Wt ratio of the propulsion system. This involves consideration of technologies that can provide high performance with reduced weight. Consider federated versus integrated technology solutions to determine what benefit a proposed technology has to enabling a higher HP/Wt ratio. •Adaptability: This is defined as the propulsion system's ability to effectively respond to changing ambient conditions to enable high performance and/or improved durability across the envelope. This would include (but not be limited to) design aspects such as intelligent components (ability to turn on/off systems as needed) and variable components (ability to actively or passively manage performance per environmental conditions). •Durability: This is defined as the ability of the propulsion system to sustain high levels of performance in adverse operating conditions for the entire design life spectrum. Consider technologies that enable the engine to maintain performance in conditions that vary from hot, sandy environments to cold environments. This will include consideration of sand tolerance technologies, ruggedized component technologies, and technologies that add to the operational life of the propulsion system. •Sustainability: This is defined as the ability of the propulsion system to maintain high performance over a prolonged operational period without requiring maintenance. Consider technologies that enhance and adapt engine performance based on prognostic and diagnostic data to facilitate an extended maintenance free period of operation of the propulsion system while increasing the ease of maintenance and reducing overall maintenance time. •Lifecycle Cost: Consider how the design of the proposed technologies will impact the overall lifecycle costs associated with propulsion systems. This will include consideration of maintenance cost and production cost. Variable speed power turbine and components necessary to enable wide variable speed power turbine operation (per the goals of this solicitation) shall be considered to be of higher value than individual additional component demonstrations. The overall net value of the proposed technology suite towards addressing the goals and characteristics of the solicitation will be evaluated. It is the responsibility of the offeror to substantiate the contributions of proposed component technologies towards achievement of the solicitation goals and characteristics within their technical proposal. All additional component demonstrations shall adhere to the lifing goals as outlined in the variable speed power turbine goals. 3.0 CALL SPECIFIC INSTRUCTIONS This call will use the Proposal Submission Process as described in 5.2 of the Broad Agency Announcement, as further supplemented below: 3.1Proposal Instructions Specific instructions pertaining to the content and structure of provided proposals are provided in the BAA, W911W6-16-R-0004, paragraph 5.2.2 and 5.2.3. In addition to the content required, the offeror shall provide the following: Volume 1 - Technical Proposal: The technical proposal shall provide a clear justification for the selection of the proposed ACE technologies. The justification/rationale supporting the proposed technologies shall be based upon the extent to which the proposed technologies contribute to the goals and characteristics identified in Section 2.0. The offeror shall substantiate their ability to achieve the goals and characteristics identified in Section 2.0 and to achieve any other benefits of the proposed technologies identified by the offeror. The offeror shall substantiate how all of the proposed technologies will sustain mechanical integrity and performance across the operating envelope. The offeror shall include a full power turbine map for their proposed variable speed power turbine as part of the proposal. This power turbine map will encompass altitudes 0 - 25,000 ft and 55% - 105% power turbine speed in accordance with the goals of Section 2.0. The power turbine map should be supplemented with a table of power turbine efficiency across the goal range as well. The offeror shall clearly define their test plans (inclusive of duration, test articles, sets of hardware, types of test, test facilities, and preliminary instrumentation definition) to successfully demonstrate the proposed technologies to TRL 6. The proposal shall include a Statement of Research Effort (SORE) that utilizes the following general task outline: 1) Task I - Design; 2) Task II - Fabrication; 3) Task III - Validation Testing; and 4) Task IV - Management and Reporting. The offeror shall also identify how the ACE technologies are integral to its ongoing efforts to develop or support an Advanced Turbo Propulsion Plan (ATPP). Although a Government approved ATPP will eventually be required for any successful offerors, such a plan is not required in order to be eligible for an award under this solicitation. The offeror shall also provide a brief description of relevant experience and capabilities. Technical proposals are limited to 150 pages total for this Call. Pages in excess of the page limitation will not be read or evaluated. Fold-out illustrations required for reader ease are allowed, however, illustration shall be counted in 8 ½" x 11" increments (e.g., an 11" x 17" document will count as two pages). Volume 2 - Price/Cost Proposal As part of this volume, Offeror's proposing use of a TIA shall include the draft TIA, provided by the Government, with proposed changes clearly marked to facilitate evaluation. 3.2Funding Any award made from this call will be subject to availability of funds. The Government anticipates a single award beginning in the 4th quarter of the Government FY16. Anticipated Government funding is approximately $19.825M. Government fiscal year distribution is as follows: FY16 $2.3M, FY17 $3.75M, FY18 $3.275M, FY19 $3.925M, FY20 $3.625M, and FY21 $2.95M. A fiscal year funding profile shall be included in the cost proposal. Due to commercial application of this development effort, at least 50% cost share is anticipated and Technology Investment Agreements are desired. 3.3Period of Performance Offerors should clearly depict their proposed schedule. The anticipated period of performance shall not exceed sixty (60) months total (56 months for technical effort and 4 months for data/final report). 3.4 Required Reporting and Deliverables All awards under this announcement will require a kickoff meeting following award. The award will require delivery of the following items delivered in Contractor's format: (1) Program Management Plan (delivered 45 days after contract award), (2) Design Review Briefing Charts (Preliminary and Detailed Design, and Test Readiness Review), (3) Detailed Design Report, (4) Test Plans, (5) Test Reports, (6) Quarterly Progress, Cost and Performance Reports, (7) Public Release Images and Videos as Required, (8) Final Report and (9) Final Briefing Charts. All awards will include a requirement to present the results of the work in a final briefing at Ft. Eustis, Virginia upon completion of all technical effort. 3.5 Data Rights The Government desires "Unlimited Rights", but at a minimum requires "Government Purpose Rights" as defined by DFARS Part 227, to all technical data, deliverables, and computer software developed under this program, and no limitations on the use of delivered and/or residual hardware. It is the Offeror's responsibility to clearly define the proposed data rights for technical data, computer software and each deliverable. Ambiguities will be negatively evaluated against the Offeror. 4.0 ORDER OF PRECEDENCE Any inconsistency between this Call and the Master BAA shall be resolved by giving precedence to this Call ((W911W6-16-R-0006). 5.0OTHER INFORMATION Additional Proposal Instructions: Technical and cost proposals shall be provided in original plus 1 paper copy and one electronic copy (CD ROM disk format). The cost proposal shall be provided in Excel format for cost verification purposes. Electronic submission of proposals is not authorized under this Call. Proposals shall be submitted to AATD, Attn: CCAM-RDT, Kenny Hood, Bld. 401 Lee Blvd., Fort Eustis, VA 23604-5577. Questions may be submitted in writing via email to Kenny Hood, kenneth.m.hood.civ@mail.mil. All questions must be submitted no later than 4 April 2016 to ensure a response. All questions and responses received will be posted to FedBizzOpps as an amendment to the call. Proposals received after the date and time specified for closing will be handled in accordance with FAR 52.215-1, Instructions to Offerors - Competitive Acquisition. This call is issued subject to the availability of funds. Proposals shall be received not later than 11April 2016; 2:00PM local (Fort Eustis) time.
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