Hung D. Nguyen and Gynelle C. Steele

Glenn Research Center, Cleveland, Ohio

Dean W. Bitler

Stinger Ghaffarian Technologies, Inc., Cleveland, Ohio

An Overview of SBIR Phase 2 Airbreathing

Propulsion Technologies

NASA/TM—2014-218497

November 2014
NASA STI Program . . . in Pro¿ le

Since its founding, NASA has been dedicated to the 

advancement of aeronautics and space science. The 

NASA Scienti¿ c and Technical Information (STI) 

program plays a key part in helping NASA maintain 

this important role.

The NASA STI Program operates under the auspices 

of the Agency Chief Information Of¿ cer. It collects, 

organizes, provides for archiving, and disseminates 

NASA’s STI. The NASA STI program provides access 

to the NASA Aeronautics and Space Database and 

its public interface, the NASA Technical Reports 

Server, thus providing one of the largest collections 

of aeronautical and space science STI in the world. 

Results are published in both non-NASA channels 

and by NASA in the NASA STI Report Series, which 

includes the following report types:

• TECHNICAL PUBLICATION. Reports of 

completed research or a major signi¿ cant phase 

of research that present the results of NASA 

programs and include extensive data or theoretical 

analysis. Includes compilations of signi¿ cant 

scienti¿ c and technical data and information 

deemed to be of continuing reference value. 

NASA counterpart of peer-reviewed formal 

professional papers but has less stringent 

limitations on manuscript length and extent of 

graphic presentations.

• TECHNICAL MEMORANDUM. Scienti¿ c 

and technical ¿ ndings that are preliminary or 

of specialized interest, e.g., quick release 

reports, working papers, and bibliographies that 

contain minimal annotation. Does not contain 

extensive analysis.

• CONTRACTOR REPORT. Scienti¿ c and 

technical ¿ ndings by NASA-sponsored 

contractors and grantees.

• CONFERENCE PUBLICATION. Collected 

papers from scienti¿ c and technical 

conferences, symposia, seminars, or other 

meetings sponsored or cosponsored by NASA.

• SPECIAL PUBLICATION. Scienti¿ c, 

technical, or historical information from 

NASA programs, projects, and missions, often 

concerned with subjects having substantial 

public interest.

• TECHNICAL TRANSLATION. Englishlanguage translations of foreign scienti¿ c and 

technical material pertinent to NASA’s mission.

Specialized services also include creating custom 

thesauri, building customized databases, organizing 

and publishing research results.

For more information about the NASA STI 

program, see the following:

• Access the NASA STI program home page at 

http://www.sti.nasa.gov

• E-mail your question to help@sti.nasa.gov

• Fax your question to the NASA STI 

Information Desk at 443–757–5803

• Phone the NASA STI Information Desk at

 443–757–5802

• Write to:

 STI Information Desk

 NASA Center for AeroSpace Information

 7115 Standard Drive

 Hanover, MD 21076–1320
Hung D. Nguyen and Gynelle C. Steele

Glenn Research Center, Cleveland, Ohio

Dean W. Bitler

Stinger Ghaffarian Technologies, Inc., Cleveland, Ohio

An Overview of SBIR Phase 2 Airbreathing

Propulsion Technologies

NASA/TM—2014-218497

November 2014

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135
Available from

NASA Center for Aerospace Information

7115 Standard Drive

Hanover, MD 21076–1320

National Technical Information Service

5301 Shawnee Road

Alexandria, VA 22312

Available electronically at http://www.sti.nasa.gov

Trade names and trademarks are used in this report for identi¿ cation 

only. Their usage does not constitute an of¿ cial endorsement, 

either expressed or implied, by the National Aeronautics and 

Space Administration.

Level of Review: This material has been technically reviewed by technical management. 
Abstract

Technological innovation is the overall focus of NASA’s Small Business Innovation Research 

(SBIR) program. The program invests in the development of innovative concepts and 

technologies to help NASA’s mission directorates address critical research and development 

needs for agency projects.

This report highlights innovative SBIR Phase II projects from 2007-2012 specifically addressing 

areas in Airbreathing Propulsion which is one of six core competencies at NASA Glenn 

Research Center. There are twenty technologies featured with emphasis on a wide spectrum of 

applications such as with a Turbo-Brayton cryocooler for aircraft superconducting systems, 

braided composite rotorcraft structures, engine air brake, combustion control valve, flexible 

composite driveshaft, and much more. Each article in this booklet describes an innovation, 

technical objective, and highlights NASA commercial and industrial applications.

This report serves as an opportunity for NASA personnel including engineers, researchers, and 

program managers to learn of NASA SBIR’s capabilities that might be crosscutting into this 

technology area. As the result, it would cause collaborations and partnerships between the small 

companies and NASA Programs and Projects resulting in benefit to both SBIR companies and 

NASA. 

An Overview of SBIR Phase 2 Airbreathing 

Propulsion Technologies 

Hung D. Nguyen and Gynelle C. Steele 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 44135 

Dean W. Bitler 

Stinger Ghaffarian Technologies, Inc. 

Cleveland, Ohio 44135 

NASA/TM—2014-218497 1
A Turbo-Brayton Cryocooler for 

Aircraft Superconducting Systems 

Designed to lower aircraft emissions, fuel consumption, 

and noise

Hybrid turboelectric aircraft—with gas turbines driving electric generators 

connected to electric propulsion motors—have the potential to transform 

aircraft design. Decoupling power generation from propulsion enables 

innovative aircraft designs, such as blended-wing bodies, with distributed 

propulsion. These hybrid turboelectric aircraft have the potential to significantly reduce emissions, decrease fuel burn, and reduce noise, all of which are 

required to make air transportation growth projections sustainable. The power 

density requirements for these electric machines can only be achieved with 

superconductors, which in turn require lightweight, high-capacity cryocoolers.

Creare, Inc., designed, built, and tested two compact, lightweight, highperformance recuperators for the Cryoflight turbo-Brayton cryocooler. This 

will provide an enabling technology for the superconducting systems needed 

for hybrid turboelectric aircraft to be feasible.

Applications

NASA photo

NASA 

The highly reliable and space-proven 

turbo-Brayton cryocooler is ideal for 

the following NASA applications: 

` Aircraft demonstrations:

t Design trade studies

t System demonstrations

t Superconducting aircraft

demonstrations

` Cryogen liquefaction and storage 

for:

t Planetary and extraterrestrial

exploration missions

t Crew exploration vehicles

t Extended-life orbital transfer

vehicles

t Inspace propellant depots

t Extraterrestrial bases

` Cooling for spaceport cryogen 

storage and transportation 

systems:

t Demonstrations of hydrogen

production and transportation 

systems

Commercial

The cryocooler is ideally suited for 

situations where high-temperature 

superconducting (HTS) materials are 

used, including: 

` Power conditioning and power 

transmission systems

` Large-scale offshore wind 

turbines

` High-efficiency data centers

` Navy ship systems

` Turboelectric aircraft

Beyond HTS, this technology 

also can be used in the following 

applications:

` Cooling for laboratory and 

industrial-scale gas separation, 

liquefaction, cryogen storage, and 

cryogen transportation systems

` Liquid hydrogen fuel cell storage 

for the automotive industry

` Commercial orbital transfer 

vehicles and satellites

Phase II Objective

` Develop and demonstrate a 

compact, lightweight recuperator 

optimized for a turbo-Brayton 

cryocooler for hybrid turboelectric 

aircraft 

)LULÄ[Z

` Reduces CO2 emissions

` Decreases fuel consumption

` Lowers noise

Firm Contact

Creare, Inc.

Anthony Dietz

P.O. Box 71

Hanover, NH 03755–3116

Phone: 603–643–3800

Fax: 603–643–4657 

Proposal Number: 11-2: A2.01-9150

NASA/TM—2014-218497 2
Braided Composite Technologies 

for Rotorcraft Structures 

To reduce weight, noise, and vibration 

A&P Technology has developed a braided material approach for fabricating 

lightweight, high-strength hybrid gears for aerospace drive systems. The 

conventional metallic web was replaced with a composite element made from 

A&P’s quasi-isotropic braid. The 0°, +/–60° braid architecture was chosen 

so that inplane stiffness properties and strength would be nearly equal in all 

directions. 

The test results from the Phase I Small Spur Gear program demonstrated 

satisfactory endurance and strength while providing a 20 percent weight 

savings. (Greater weight savings is anticipated with structural optimization.) 

The hybrid gears were subjected to a proof-of-concept test of 1 billion cycles 

in a gearbox at 10,000 revolutions per minute and 490 in-lb torque with no 

detectable damage to the gears. After this test the maximum torque capability 

was also tested, and the static strength capability of the gears was 7x the 

maximum operating condition. Additional proof-of-concept tests are in 

progress using a higher oil temperature, and a loss-of-oil test is planned. 

The success of Phase I led to a Phase II program to develop, fabricate, and 

optimize full-scale gears, specifically Bull Gears. The design of these Bull 

Gears will be refined using topology optimization, and the full-scale Bull 

Gears will be tested in a full-scale gear rig. The testing will quantify benefits 

of weight savings, as well as noise and vibration reduction. The expectation is 

that vibration and noise will be reduced through the introduction of composite material in the vibration transmission path between the contacting gear 

teeth and the shaft-and-bearing system.

Applications

Accelerometers

Driver gear

Loaded gear

NASA 

` Rotorcraft systems

Commercial

This technology could be applied 

to gears across many consumer 

industries, including: 

` Aviation

` Industrial 

` Automotive

Phase II Objectives

` Determine operating conditions for 

a gear in a rotorcraft gearbox

` Develop, fabricate, and optimize 

full-scale composite/metal hybrid 

gears for full-scale validation testing

` Evolve analytical tools to enable 

design optimization 

)LULÄ[Z

` Decreased weight in rotorcraft 

gearboxes

` Reduced noise and vibration

Firm Contact

A&P Technology

Nathan Jessie

4595 East Tech Drive

Cincinnati, OH 45245–1055

Phone: 513–688–3200

Fax: 513–688–3201

Proposal Number: 11-2: A2.09-8194

NASA/TM—2014-218497 3
Deployable Engine Air Brake

For quiet drag management

On approach, next-generation aircraft are likely to have airframe noise levels 

that are comparable to or in excess of engine noise. ATA Engineering, Inc. 

(ATA) is developing a novel quiet engine air brake (EAB), a device that 

generates “equivalent drag” within the engine through stream thrust 

reduction by creating a swirling outflow in the turbofan exhaust nozzle. 

Two Phase II projects were conducted to mature this technology: 

(1) a concept development program (CDP) and (2) a system development 

program (SDP).

Concept Development Program

The CDP used computational fluid dynamics 

to quantify the relationship between flow, 

thrust, and equivalent drag for a number 

of EAB geometries designed by ATA. A 

model-scale prototype was designed and built 

for experimental aeroacoustics assessment in NASA’s 

Aeroacoustic Propulsion Laboratory. Flyover simulations 

using NASA’s Aircraft Noise Prediction Program suggested the 

technology could enable, for example, a steep approach trajectory 

(from a baseline 3.2° glideslope to 4.4°) for a 737-800-class aircraft, resulting 

in a peak tone-corrected perceived noise level reduction of up to 3.1 dB.

System Demonstration Program

The system demonstration program (SDP) currently underway includes 

detailed design and fabrication of a mechanical EAB prototype to be used 

in demonstrating a system that can seamlessly switch between stowed and 

deployed modes while the engine outlet nozzle is charged with a highpressure flow stream. That is, the system will include a mechanism to allow 

swirl-inducing vanes to be stowed within the engine structure, facilitating 

normal flow during cruise conditions and deployment on demand to reduce 

the engine’s thrust while maintaining flow capacity. To demonstrate the 

technology on a relevant platform, the prototype is being designed to integrate with Williams International’s FJ44-4 mixed-flow turbofan, a 

family of engines that supports a variety of business 

jet customers, such as the Cessna 

CJ4, Hawker 400XPR, and 

Pilatus PC-24. 

CDP Phase II Objectives

` Design and build a stationary 

model-scale EAB simulator for 

performance and noise testing

` Quantify relationship between swirl 

vane angle, equivalent drag, fan 

and core stream flow, and noise for 

a representative high bypass ratio 

engine

` Evaluate how the performance of 

an EAB is affected by deflection of 

the engine pylon trailing edge 

` Assess system noise reduction 

potential via flyover simulation

Proposal Number: 07-2: A2.03-8606

NASA illustration

NASA illustration

NASA/TM—2014-218497 4
Planned On-Engine Testing

The mechanical EAB prototype will be ground tested for functional, thrust 

reduction, and noise performance when installed on an FJ44-4 turbofan engine. 

The engine’s operational parameters will also be measured over a range of throttle 

settings with the EAB at stowed, deployed, and intermediate points to ensure 

adequate surge margin at all operating conditions. Acoustic measurements will 

quantify the noise difference between the stowed and deployed states. Stresses, 

temperatures, and pressures within the engine will be monitored to validate 

normal operation. The operational test program is slated to be performed at 

Williams International’s Outdoor Test Facility in mid-2015.

Applications

NASA 

` Promote feasibility of nextgeneration quiet aircraft 

concepts:

t Tube and wing (current

generation +1)

t Integrated airframe

propulsion system

configurations (current

generation +2)

Commercial

` Existing aircraft:

t Incorporate technology

through retrofit (ejector) hush

kits on older aircraft engines

in order to meet current and

future noise requirements

` Future aircraft:

t Modify traditional engine exit

guide vanes or bypass nozzles

with a variable mechanism

that generates a swirling

outflow in drag management

mode

)LULÄ[Z

` Enables slower and/or steep 

approaches, thereby locating the 

noise source farther from affected 

communities below the flight path

` Reduces aircraft approach noise 

by creating “drag on demand,” 

without the associated unsteady 

flow structures of devices such as 

flaps, slats, and undercarriage

` Can be rapidly stowed in a 

go-around event

SDP Phase II Objectives

` Development of a design 

specification for an FJ44-4 EAB

` Preliminary and detailed aero and 

mechanical design of a mechanical 

EAB prototype

` Hardware fabrication, assembly, 

and bench testing

` Operational testing of hardware on 

FJ44-4 engine

Firm Contact

ATA Engineering, Inc.

Joshua Davis

13290 Evening Creek Drive South, Suite 250

San Diego, CA 92128

Phone: 858–480–2028

Fax: 858–792–8932

Proposal Number: 11-2: A2.03-9148

NASA/TM—2014-218497 5
High-Fidelity Simulation of Jet 

Noise From Rectangular Nozzles 

Large eddy simulation (LES) model for noise reduction in 

advanced jet engines and automobiles

This Phase II project validated a state-of-the-art LES model, coupled with a 

Ffowcs Williams–Hawkings (FW-H) far-field acoustic solver, to support the 

development of advanced engine concepts. These concepts include innovative 

flow control strategies to attenuate jet noise emissions. The end-to-end LES/

FW-H noise prediction model was demonstrated and validated by applying 

it to rectangular nozzle designs with a high aspect ratio. The model also was 

validated against acoustic and flow-field data from a realistic jet-pylon 

experiment, thereby significantly advancing the state of the art for LES.

Applications

AS NA p hoto

NASA 

` Supersonic aircraft:

t High-fidelity LES modeling

for noise control

t Testing of scale-model single

or dual rectangular nozzles

t Testing of nozzles with

chevrons and bevels

` Subsonic fixed-wing aircraft:

t Testing of high aspect ratio

rectangular nozzles

Commercial

` U.S. Navy:

t Noise suppression technology

for the F/A-18E/F and Joint 

Strike Fighter F-35B programs

t Retrofits for F414-400 engine,

F404-400 engine, and 

F/A-18C/D aircraft

t High-fidelity modeling for

next-generation propulsion 

systems

` Automotive:

t High-fidelity predictive tools

for noise reduction caused by 

vortex shedding of side-view 

mirrors

Phase II Objectives

` Upgrade the LES for accurate 

interfacing with the nozzle internal 

flow field, including the effects 

of the nozzle boundary layer 

turbulence on initial shear layer 

growth

` Rectify overprediction of initial 

turbulent velocity statistics at the 

nozzle lipline

` Validate the LES/FW-H for 

performing flow-field predictions 

of high aspect ratio rectangular 

and bevel nozzle free jets using 

detailed flow-field and acoustic 

measurements 

` Provide validation of the LES/

FW-H model for predicting noise 

emissions for a real-world engine 

installation with effects of pylon on 

far-field noise 

)LULÄ[Z

` Provides highly predictive modeling

` Reduces noise in jet engines and 

automobiles

Firm Contact

Combustion Research and 

 Flow Technology, Inc.

Neeraj Sinha

sinha@craft-tech.com

6210 Keller’s Church Rd.

Pipersville, PA 18947–1020

Phone: 215–766–1520 ext.16

Proposal Number: 10-2: A2.03-9826

NASA/TM—2014-218497 6
Microtextured Surfaces for Turbine 

Blade Impingement Cooling 

Provides more effective internal impingement cooling

Gas turbine engine technology is constantly challenged to operate at higher 

combustor outlet temperatures. In a modern gas turbine engine, these 

temperatures can exceed the blade and disk material limits by 600 °F or more, 

necessitating both internal and film cooling schemes in addition to the use of 

thermal barrier coatings. Internal convective cooling is inadequate in many 

blade locations, and both internal and film cooling approaches can lead to 

significant performance penalties in the engine.

Micro Cooling Concepts, Inc., has developed a turbine blade cooling concept 

that provides enhanced internal impingement cooling effectiveness via the use 

of microstructured impingement surfaces. These surfaces significantly increase 

the cooling capability of the impinging flow, as compared to a conventional 

untextured surface. This approach can be combined with microchannel 

cooling and external film cooling to tailor the cooling capability per the 

external heating profile. The cooling system then can be optimized to 

minimize impact on engine performance. 

Applications

NASA 

` Turbine engine development

` Versatile Affordable Advanced 

Turbine Engine (VAATE) 

initiative

` Two-stage-to-orbit designs

Commercial

` Military and commercial aircraft:

t Enables higher combustion

temperatures with lower 

engine penalties

` Power generation plants:

t Enables operation at higher

temperatures and efficiencies

` Electronics

` Industrial processes

` Automotive

` Lasers

Phase II Objective

` Evaluate the suitability of hightemperature materials (e.g., from 

the Inconel® or HAYNES® series) in 

this application.

)LULÄ[Z

` Increases cooling capability of the 

impinging flow

` Enables tailored cooling capability

Firm Contact

Micro Cooling Concepts, Inc. 

Jack Fryer

jayfryer@microcoolingconcepts.com

7522 Slater Avenue, #122

Huntington Beach, CA 92647–7738

Phone: 714–847–9945 

Proposal Number: 10-2: A2.10-8672 Inconel is a registered trademark of Special Metals Corp. 

HAYNES is a live, registered trademark of Haynes International, Inc.

NASA/TM—2014-218497 7
Real-Time Aircraft 

Engine-Life 

Monitoring 

For real-time health monitoring of aircraft engine 

components and systems

This project developed an inservice life-monitoring system capable of 

predicting the remaining component and system life of aircraft engines. 

The embedded system provides real-time, inflight monitoring of the engine’s 

thrust, exhaust gas temperature, efficiency, and the speed and time of 

operation. Based upon this data, the life-estimation algorithm calculates the 

remaining life of the engine components and uses this data to predict the 

remaining life of the engine. The calculations are based on the statistical life 

distribution of the engine components and their relationship to load, speed, 

temperature, and time. 

Applications

NASTEC photo ASTEC photo

NASA 

` Aircraft engine performance

Commercial

` Aviation and aerospace:

t Inflight monitoring system

analyzes remaining service life 

of aircraft engine

Phase II Objectives

` Acquire profiles of aircraft system 

engines

` Develop a complete embedded 

hardware/software system 

architecture

` Verify the system design in 

simulation

` Integrate the life monitor into a 

commercial or military aircraft 

)LULÄ[Z

` More accurately predicts remaining 

component and system life of 

aircraft engines

` Improves aviation safety, reliability, 

and maintenance

` Reduces life-cycle costs and 

maintenance costs

` Facilitates cost-effective design and 

manufacturing of new production 

engines

Firm Contact

Nastec, Inc.

Richard Klein, President & CEO

dickc123@earthlink.net 

5310 W. 161st Street, Suite G

Brook Park, OK 44142–1601

Phone: 216–464–8388

Proposal Number: 09-2: A1.08-9406

NASA/TM—2014-218497 8
Inflight and Preflight 

Detection of Pitot Tube 

Anomalies 

Increases the safety of aircraft passengers and crew

The health and integrity of aircraft sensors play a critical role in aviation 

safety. Inaccurate or false readings from these sensors can lead to improper 

decision making, resulting in serious and sometimes fatal consequences. This 

project demonstrated the feasibility of using advanced data analysis techniques 

to identify anomalies in Pitot tubes resulting from blockage such as icing, 

moisture, or foreign objects. 

The core technology used in this project is referred to as noise analysis because 

it relates sensors’ response time to the dynamic component (noise) found 

in the signal of these same sensors. This analysis technique has used existing 

electrical signals of Pitot tube sensors that result from measured processes 

during inflight conditions and/or induced signals in preflight conditions to 

detect anomalies in the sensor readings.

Analysis and Measurement Services Corporation (AMS Corp.) has routinely 

used this technology to determine the health of pressure transmitters in 

nuclear power plants. The application of this technology for the detection of 

aircraft anomalies is innovative. Instead of determining the health of process 

monitoring at a steady-state condition, this technology will be used to quickly 

inform the pilot when an air-speed indication becomes faulty under any flight 

condition as well as during preflight preparation.

Applications

NASA photo

NASA 

` Pitot tube/static system 

performance

Commercial

` Aviation and aerospace:

t Detection of Pitot tube

anomalies resulting from

blockages during inflight or

preflight conditions

t Wide applications in commercial, private, and military

aircraft industries

t Applicable to new aircraft

and existing aircraft with only

minor modifications

Phase II Objectives

` Research and acquire existing air 

data systems and evaluate them 

for compatibility with the proposed 

signal analysis techniques

` Complete laboratory experiments 

to identify the signal analysis 

techniques that best distinguish 

Pitot tube blockage

` Develop and optimize the inflight 

blockage detection algorithm and 

software

` Develop and build inflight blockage 

detection prototype system

` Develop and build preflight blockage 

detection prototype system

` Demonstrate and validate prototype 

blockage detection system through 

inflight testing 

)LULÄ[Z

` Improves detection of inaccurate 

indications

` Increases safety of passengers 

and crew

` Reduces the potential for 

accidents

Firm Contact

Darrell W. Mitchell

darrell@ams-corp.com

9119 Cross Park Drive

Knoxville, TN 37923–4510

Phone: 865–691–1756

Proposal Number: 09-2: A1.10-8957

NASA/TM—2014-218497 9
Lightweight, Efficient Power 

Converters for Advanced 

Turboelectric Aircraft Propulsion 

Systems

Extremely efficient cryogenic power conversion technology

NASA is investigating advanced turboelectric aircraft propulsion systems 

that use superconducting motors to drive multiple distributed turbofans. 

Conventional electric motors are too large and heavy to be practical for 

this application; therefore, superconducting motors are required. In order 

to improve aircraft maneuverability, variable-speed power converters are 

required to throttle power to the turbofans. The low operating temperature 

and the need for lightweight components that place a minimum of additional 

heat load on the refrigeration system open the possibility of incorporating 

extremely efficient cryogenic power conversion technology. This Phase II 

project is developing critical components required to meet these goals.

Applications

NASA 

` Turboelectric aircraft 

propulsion systems

` High-power drives for 

superconducting motors

` High-power and high-powerdensity cryogenic and wide 

temperature range power 

conversion systems:

t Interplanetary and interstellar

spacecraft

t Satellites

t Landers

t Surface base stations on

moons or planets

Commercial/Other 

Government

` Utility projects to develop superconducting power transmission

` Superconducting wind turbine 

generators

` Distribution systems for large 

buildings (e.g., data centers, 

manufacturing plants):

t MTECH Laboratories is

currently working toward a

demonstration site of such

a distribution system

` U.S. Navy:

t Cryogenic motor drive system

for the All-Electric Ship

program

` U. S. Department of Energy 

(DOE):

t Equipment for superconducting accelerators at DOE

national accelerator labs

Phase II Objectives

` Design, fabricate, and test a 

cryogenic multichip module, 

which can be used in applications 

requiring very high power densities 

and efficiencies

` Design, fabricate, and test a 

cryogenic half-bridge inverter using 

these modules, demonstrating 

the potential reduction in size and 

weight for a given power level as 

well as ultrahigh efficiency 

)LULÄ[

` Offers small size, low weight, 

and high efficiency

Firm Contact

MTECH Laboratories, LLC 

Michael J. Hennessy

mjhennessy@mtechlabs.com

831 Rte. 67, Bldg. 45C

Ballston Spa, NY 12020–0227

Phone: 518–885–6436

Proposal Number: 09-2: A2.01-9471 

NASA/TM—2014-218497 10
Novel Active Combustion 

Control Valve

For high-frequency modulation of atomized fuel flow 

This project presents an innovative solution for active combustion control. 

Relative to the state of the art, this concept provides frequency modulation 

(greater than 1,000 Hz) in combination with high-amplitude modulation (in 

excess of 30 percent flow) and can be adapted to a large range of fuel injector 

sizes. Existing valves often have low flow modulation strength. To achieve 

higher flow modulation requires excessively large valves or too much electrical 

power to be practical. This active combustion control valve (ACCV) has 

high-frequency and -amplitude modulation, consumes low electrical power, is 

closely coupled with the fuel injector for modulation strength, and is practical 

in size and weight. By mitigating combustion instabilities at higher frequencies 

than have been previously achieved (~1,000 Hz), this new technology enables 

gas turbines to run at operating points that produce lower emissions and 

higher performance.

Applications

AS N p Aot ho

NASA 

` This technology can be used 

in engine designs for higher 

performance and lower exhaust 

emissions for:

t Prime propulsion

t Auxiliary power

t Power generation

Commercial

` Large-frame power generating 

gas turbine manufacturers 

` Low-emission combustion 

systems

Phase II Objectives

` Use analysis and design tools to 

refine and optimize the ACCV and its 

associated components, including 

the motor, electronic controller, and 

proportional solenoid

` Finalize the design and generate 

hardware drawings

` Manufacture the ACCV components 

and assemble the various components 

into working prototype units

` Test the ACCV to validate its fuel flow 

modulation strength and frequency 

response up to 1,000 Hz

` Reduce the test data and determine 

the effectiveness of the ACCV at 

modulating fuel flow at 1,000 Hz

` Validate analysis models 

)LULÄ[Z

` Mitigates combustion instabilities at 

higher frequencies

` Can be close-coupled to the atomizer 

for high-modulation strength

` Consumes low electrical power

` Offers compact and lightweight design

Firm Contact

Jansen’s Aircraft Systems Controls Inc. 

Matt Caspermeyer

matt.caspermeyer@jasc-controls.com

2303 West Alameda Dr.

Tempe, AZ 85282–3102

Phone: 602–889–3711

Proposal Number: 09-2: A2.02-9291 

NASA/TM—2014-218497 11
Ultrahigh Temperature 

Capacitive Pressure Sensor

To monitor engine health and improve aircraft safety

Robust, miniaturized sensing systems are needed to improve performance, 

increase efficiency, and track system health status and failure modes of 

advanced propulsion systems. Because microsensors must operate in extremely 

harsh environments, there are many technical challenges involved in developing reliable systems. In addition to high temperatures and pressures, sensing 

systems are exposed to oxidation, corrosion, thermal shock, fatigue, fouling, 

and abrasive wear. In these harsh conditions, sensors must be able to withstand 

high flow rates, vibration, jet fuel, and exhaust. In order for existing and 

future aeropropulsion turbine engines to improve safety and reduce cost and 

emissions while controlling engine instabilities, more accurate and complete 

sensor information is necessary. High-temperature (300 to 1,350 °C) 

capacitive pressure sensors are of particular interest due to their high 

measurement bandwidth and inherent suitability for wireless readout schemes. 

The objective of this project is to develop a capacitive pressure sensor based 

on silicon carbon nitride (SiCN), a new class of high-temperature ceramic 

materials, which possesses excellent mechanical and electric properties at 

temperatures up to 1,600 °C. 

Applications

NASA 

` Planetary exploration mission to 

Venus

` Integrated vehicle health management and control for onboard 

systems:

t Propulsion systems, including

launch and station-keeping,

turbo pump assemblies, thrust

chamber assemblies in liquid

rocket motors, and nuclear

thermal propulsion

` Energy generation systems, such 

as fuel cells, Stirling engines, and 

nuclear reactors 

` In situ resource utilization 

systems

Commercial

` Commercial and military jets

` Fossil fuel (coal and natural gas) 

power generation

` Nuclear power generation

` Concentrating solar thermal 

power generation

Phase II Objectives

` Optimize SiCN formulations to create 

materials with optimized dielectric and 

loss tangent properties

` Develop an SiCN device fabrication 

process to realize air/electrode gap 

sizes of less than 5 μm

` Fabricate improved prototype SiCN 

sensor devices, prototype packaging 

hardware, and signal conditioning 

electronics

` Perform laboratory-scale performance 

testing

` Based on results of initial integrated 

hardware testing, redesign and rebuild 

prototype hardware for relevant 

environment testing in NASA and/

or partner test systems to achieve a 

technology readiness level (TRL) 5–6 

)LULÄ[Z

` Significantly reduces payload weight 

and volume

` Enables enhanced health monitoring 

via a noninvasive, on-engine system

` Does not require cooling

Firm Contact

Sporian Microsystems, Inc. 

Kevin Harsh

harshk@sporian.com

515 Courtney Way, Suite B

Lafayette, CO 80026–8821

Phone: 303–516–9075 ext. 12

Proposal Number: 09-2: A2.02-9410 

NASA/TM—2014-218497 12
Simulation Tool for Dielectric 

Barrier Discharge Plasma 

Actuators

Can be used at atmospheric and subatmospheric pressures 

Traditional approaches for active flow separation control using dielectric 

barrier discharge (DBD) plasma actuators are limited to relatively low speed 

flows and atmospheric conditions. This results in low feasibility of the DBDs 

for aerospace applications. For active flow control at turbine blades, fixed 

wings, and rotary wings and on hypersonic vehicles, DBD plasma actuators 

must perform at a wide range of conditions, including rarified flows and 

combustion mixtures. An efficient, comprehensive, physically based DBD 

simulation tool can optimize DBD plasma actuators for different operation 

conditions. 

Researchers are developing a DBD plasma actuator simulation tool for a wide 

range of ambient gas pressures. The tool will treat DBD using either kinetic, 

fluid, or hybrid models, depending on the DBD operational condition.

Applications

NASA 

` Active flow separation control:

t Subsonic and hypersonic

flights

` Optimize gas discharges at 

different ambient pressures 

(e.g., plasma-assisted combustion 

for the reduction of carbon 

emissions)

Commercial

` Active flow separation control 

for subsonic and hypersonic 

programs:

t Flow separation control for

commercial airplanes during 

takeoff or landing

t Active flow control for hypersonic vehicles 

t Increase in lift for tiltrotor

aircraft

t Improvement of engine

performance

` Plasma aerodynamics applications:

t Plasma-assisted combustion

t Flow control using different

types of discharges

t Reduction of carbon emission

t Optimization of air vehicle

operation

t Magnetohydrodynamic

(MHD) and electrohydrodynamic (EHD) applications

t Plasma processing and plasma

medicine

Phase II Objectives

` Extend chemical and physical 

discharge model in VORPAL®

software application

` Extend hybrid capabilities of the 

proposed model

` Enhance computational speed of 

the proposed DBD simulation tool

` Demonstrate the DBD simulation 

tool through validation against 

experimental data at a wide range 

of DBD operational conditions 

)LULÄ[Z

` Provides an efficient and effective 

simulation tool for DBD plasma 

actuators

` Is optimized for a wide range of 

ambient gas pressures

Firm Contact

Tech-X Corporation

Alexander Likhanskii

likhansk@txcorp.com

5621 Arapahoe Ave

Boulder, CO 80303–1379

Phone: 303–996–7520

Proposal Number: 09-2: A2.05-9058 VORPAL is a registered trademark of the 

University of Colorado.

NASA photo

NASA/TM—2014-218497 13
Design Environment for 

Multifidelity and Multidisciplinary 

Components

An integrated framework for turbomachinery analysis

One of the greatest challenges when developing propulsion systems is 

predicting the interacting effects between the fluid loads, thermal loads, and 

structural deflection. The interactions between technical disciplines often are 

not fully analyzed, and the analysis in one discipline often uses a simplified 

representation of other disciplines as an input or boundary condition. For 

example, the fluid forces in an engine generate static and dynamic rotor 

deflection, but the forces themselves are dependent on the rotor position 

and its orbit. It is important to consider the interaction between the physical 

phenomena where the outcome of each analysis is heavily dependent on the 

inputs (e.g., changes in flow due to deflection, changes in deflection due to 

fluid forces). A rigid design process also lacks the flexibility to employ multiple 

levels of fidelity in the analysis of each of the components. 

This project developed and validated an innovative design environment that 

has the flexibility to simultaneously analyze multiple disciplines and multiple 

components with multiple levels of model fidelity. Using NASA’s open-source 

multidisciplinary design analysis and optimization (OpenMDAO) framework, 

this multifaceted system will provide substantially superior capabilities to 

current design tools.

Applications

NASA 

` Integrated framework for 

turbomachinery analysis

` Multifidelity physics-based tools

` Numeric zoom functions in 

numerical propulsion system 

simulation (NPSS):

t Fluid-structure interaction

capability

t High-fidelity analysis and

optimization in OpenMDAO

Commercial/Military

Enhanced design and 

development of:

` Gas turbine engines 

` High-performance 

turbomachinery

Phase II Objectives

` Develop and validate the modeling 

architectures for fluid structure 

interaction (FSI) analysis

` Develop FSI capability in NASA 

computational fluid dynamics 

solver and commercially available 

solver

` Verify and validate the functions 

for numeric zoom, FSI, multidiscipline, and multifidelity analysis

)LULÄ[Z

` Improves design analysis 

process of a wide range of highperformance turbomachinery (gas 

turbine and chemical propulsion, 

power generation, oil and gas)

` Reduces failure rate and 

development cost of 

turbo-machinery systems 

` Reduces time and complexity of 

multiphysics analysis (e.g., job 

setup, solution control, pre- and 

postprocessing)

Firm Contact

Mechanical Solutions, Inc. 

Michael Platt

mjp@mechsol.com

11 Apollo Drive

Whippany, NJ 07981–1423

Phone: 973–973–9920

Proposal Number: 09-2: A2.08-8224 

NASA/TM—2014-218497 14
Embedded Data Acquisition 

Tools for Rotorcraft 

Diagnostic Sensors

To monitor and diagnose harmful vibration effects 

inherent to flight operation

Rotorcraft drive trains must withstand enormous pressure while operating 

continuously in extreme temperature and vibration environments. Captive 

components, such as planetary and spiral bevel gears, see enormous strain but 

are not accessible to fixed instrumentation, such as a piezoelectric transducer. 

Thus, it is difficult to directly monitor components that are most susceptible to 

damage. 

This innovation is a self-contained data processing unit within a specialized 

fixture that installs directly inside the rotating pinion gear in the gearbox. From 

this location, it detects and transmits high-resolution prognostic data to a fixed 

transceiver. The sensor is based on microelectromechanical systems (MEMS) 

technology and uses innovative circuit designs to capture high-bandwidth data 

and transmit it wirelessly from inside an operational helicopter transmission.

With Ridgetop’s advanced MEMS-based sensor, researchers have, for the 

first time, been able to extract high-resolution acoustic signatures wirelessly 

from sensors within the transmission that would otherwise be muffled by 

background gear noises. Ridgetop’s innovative instrument will help researchers 

perform dynamic analysis of gear interaction and develop improved designs 

for gear components. In addition, data from this instrument can be used 

to validate new algorithms that detect and predict faults based on external 

acoustic signatures, for prognostic purposes. The result of this work will be an 

improvement in safety, performance, and cost for future generations of rotating 

components.

Applications

d Riget p oGro pu oh p ot

NASA 

` Subsonic Rotary Wing Project:

t Improved vibration sensors

to help monitor and diagnose

harmful vibration effects

Commercial

` Rotorcraft operators:

t Real-time, efficient analysis

of critical diagnostic data and

routines

` Rotorcraft manufacturers:

t Field testing measurements

of vibration and accumulated

stress

` Railway abnormal condition 

detection

` Real-time monitoring of 

downhole drill vibration in oil 

and gas exploration

` Sensing tool wear, chatter, or 

spindle balance in computer 

numerical control applications

Phase II Objectives

` Build and demonstrate module and 

acquisition system 

` Tie in data collection with prognostics and advanced diagnostic 

approaches, and show an improvement in failure detection horizon 

times

` Develop a data interface between 

the wireless sensor port and 

a standard health and usage 

monitoring systems (HUMS) 

communication bus

` Demonstrate the technology with 

airframe manufacturers

)LULÄ[Z

` Monitors structural and electronic 

stress due to vibration during flight

` Detects wear in the drive gears 

inside helicopter gearboxes

` Provides IoT (Internet of Things)-

compatible wireless technology

` Supports hundreds of nodes in a 

sensor network

` Downloads data quickly

Firm Contact

Ridgetop Group, Inc.

Robert Wagoner

rwagoner@ridgetopgroup.com

3580 West Ina Road

Tucson, AZ 85741

Phone: 520–742–3300

Proposal Number: 09-2: A2.09-9940 

NASA/TM—2014-218497 15
Design Concepts for Cooled 

Ceramic Matrix Composite 

Turbine Vanes

To reduce emissions and improve fuel consumption 

in gas turbine engines

This project demonstrated that higher temperature capabilities of ceramic 

matrix composites (CMCs) can be used to reduce emissions and improve 

fuel consumption in gas turbine engines. The work involved closely coupling 

aerothermal and structural analyses for the first-stage vane of a high-pressure 

turbine (HPT). These vanes are actively cooled, typically using film cooling. 

Ceramic materials have structural and thermal properties different from 

conventional metals used for the first-stage HPT vane. This project identified 

vane configurations that satisfy CMC structural strength and life constraints 

while maintaining vane aerodynamic efficiency and reducing vane cooling 

to improve engine performance and reduce emissions. The project examined 

modifications to vane internal configurations to achieve the desired objectives. 

Thermal and pressure stresses are equally important, and both were analyzed 

using an ANSYS® structural analysis. Three-dimensional fluid and heat transfer 

analyses were used to determine vane aerodynamic performance and heat load 

distributions.

Applications

NASA 

` Gas turbine engine applications:

t Develop new materials

to increase turbine inlet

temperatures

t Reduce vane cooling to lower

combustor outlet temperature

without decreasing rotor inlet

temperature

t Reduce specific fuel consumption and carbon dioxide

(CO2

) emissions

Commercial/Military

` Transport aircraft:

t Improve specific fuel

consumption in gas turbine

engines

` Power: 

t Reduce fuel consumption and

CO2

 emissions of gas turbines

Phase II Objectives

` Perform aerothermal analyses for the 

first-stage vane of the high-pressure 

turbine of the energy-efficient engine 

(EEE) 

` Identify benefits of reduced specific 

fuel consumption and nitric oxide 

emissions due to CMC vanes and 

blades

` Evaluate thickness, hoop, and radial 

component stresses for EEE vane

` Evaluate stresses due to pressure, 

thermal, and combined loads

` Evaluate significance of film cooling 

holes on stresses

` Evaluate stresses due to the presence 

of trailing-edge ejection cooling tubes

` Evaluate sensitivity of component 

stresses to variations in material 

properties and boundary conditions

` Evaluate radial cooling concepts for 

small engine application

)LULÄ[

` Reduces emissions and improves fuel 

consumption in gas turbine engines

Firm Contact

N&R Engineering 

Robert Boyle

rbrjboyle760@gmail.com

6659 Pearl Road, #201

Parma Heights, OH 44130–3821

Phone: 440–845–7020

Proposal Number: 09-2: A2.10-9062 ANSYS is a registered trademark of ANSYS, Inc.

NASA/TM—2014-218497 16
Blade Vibration Measurement 

System for Unducted Fans 

Provides noncontacting measurements to characterize 

unducted fan blade dynamics

With propulsion research programs focused on new levels of efficiency and 

noise reduction, two avenues for advanced gas turbine technology are emerging: 

the geared turbofan and ultrahigh bypass ratio fan engines. Both of these 

candidates are being pursued as collaborative research projects between NASA 

and the engine manufacturers. The high bypass concept from GE Aviation is an 

unducted fan that features a bypass ratio of over 30 along with the accompanying benefits in fuel efficiency. This project improved the test and measurement 

capabilities of the unducted fan blade dynamic response. In the course of this 

project, Mechanical Solutions, Inc. (MSI) collaborated with GE Aviation to (1) 

define the requirements for fan blade measurements; (2) leverage MSI’s radarbased system for compressor and turbine blade monitoring; and (3) develop, 

validate, and deliver a noncontacting blade vibration measurement system for 

unducted fans. 

Applications

NASA 

` Innovative, nonintrusive 

unducted fan blade dynamics 

measurement system

` Wind tunnel facilities

Commercial/Military

` Turbofan and turboprop engines 

` Blade health management for 

wind turbines and rotorcraft

Phase II Objectives

` Develop and validate a 

noncontacting measurement 

system for unducted fans

` Integrate system with existing 

technology at GE Aviation

` Deliver a working system to 

NASA 

)LULÄ[Z

` Offers resolution capable 

of characterizing fan blade 

dynamic modes

` Improves test and 

measurement technology

` Improves measurement capability

Firm Contact

Mechanical Solutions, Inc.

William Marscher

wdm@mechsol.com

11 Apollo Drive

Whippany, NJ 07981–1423

Phone: 973–973–9920

Proposal Number: 09-2: A4.01-8214

NASA/TM—2014-218497 17
Fast Response Shape Memory 

Effect Titanium Nickel (TiNi) 

Foam Torque Tubes 

High-speed, high-torque torsional actuators for 

aerospace applications

Shape Change Technologies has developed a process to manufacture 

net-shaped TiNi foam torque tubes that demonstrate the shape memory effect. 

The torque tubes dramatically reduce response time by a factor of 10. This 

Phase II project matured the actuator technology by rigorously characterizing 

the process to optimize the quality of the TiNi and developing a set of metrics 

to provide ISO 9002 quality assurance. A laboratory virtual instrument 

engineering workbench (LabVIEWTM)-based, real-time control of the torsional 

actuators was developed. These actuators were developed with The Boeing 

Company for aerospace applications. 

Applications

NASA 

` “Morphing” unmanned aerial 

vehicles (UAVs)

` Concept vehicles: 

t Using wing twist to control

flexible wing structures

` Deployment of booms:

t Deploying sensors in aircraft

and/or in spacecraft where 

the lightweight, minimal 

part count actuators could be 

heated electrically

` Next-generation shuttles 

(actuators must also be space 

qualified):

t Controlling wing twist,

nacelle structures, or ancillary 

aircraft structures

Commercial

` Aviation:

t Controlling variable nacelle

structures

` Windmills and turbines:

t Generating energy more

efficiently

` Health care:

t Assisting the disabled as a lift

device (similar to hydraulic 

actuators but with less bulk)

Phase II Objectives

` With Boeing: 

t Optimize materials to reduce

contamination

t Develop ISO 9002 production

standards

t Develop high-speed, high-torque

torsional actuators

` Fully characterize the materials 

mechanically and chemically during 

production to minimize oxide/

hydride contamination

` Develop LabVIEW-based 

computer-controlled actuation for 

on-off and proportional control

` Develop infrastructure to support 

batch production of actuators

` Test actuators (Boeing provides in 

its testbed facility) 

)LULÄ[Z

` Large torque

` Fast response

` More aerodynamically efficient 

structures

Firm Contact

Shape Change Technologies LLC

Peter Jardine

jardine@shape-change.com

1731 Hendrix Ave.

Thousand Oaks, CA 91360–3316

Phone: 805–805–5665

Proposal Number: 08-2: A2.01-8646 LabVIEW is a trademark of National Instruments.

NASA/TM—2014-218497 18
Integrated Multidisciplinary 

Optimization Objects

Integrated modules for constructing and solving 

multidisciplinary design analysis and optimization 

(MDAO) problems

OpenMDAO is an open-source MDAO framework. It is used to develop 

an integrated analysis and design environment for engineering challenges. 

This Phase II project integrated additional modules and design tools into 

OpenMDAO to perform discipline-specific analysis across multiple flight 

regimes at varying levels of fidelity. It also showcased a refined system 

architecture that allows the system to be less customized to a specific 

configuration (i.e., system and configuration separation). By delivering a 

capable and validated MDAO system along with a set of example applications 

to be used as a template for future users, this work greatly expands NASA’s 

high-fidelity, physics-based MDAO capabilities and enables the design of 

revolutionary vehicles in a cost-effective manner. This proposed work 

complements M4 Engineering’s expertise in developing modeling and 

simulation toolsets that solve relevant subsonic, supersonic, and hypersonic 

demonstration applications.

Applications

US Navy photo

NASA 

` MDAO:

t Exchange information

between multiple analysis 

codes at multiple levels of 

fidelity to create models of 

complex systems

t Apply state-of-the-art MDAO

algorithms designed to solve 

highly coupled problems that 

arise when multiple analysis 

tools are combined

t Quickly implement new tools

and methods for handling 

complex design problems

Commercial

` Subsonic, supersonic, and 

hypersonic demonstration 

Phase II Objectives

` Establish system design

` Integrate framework-neutral software 

library

` Implement additional analysis modules

` Implement general-purpose modules

` Validate system with example 

problems 

)LULÄ[Z

` Enables a much higher degree of 

code sharing and reuse among the 

MDAO community

` Provides a baseline set of modules 

for constructing and solving MDAO 

problems

` Integrates discipline-specific and 

common-object modules into 

OpenMDAO, including propulsion, 

noise, mission, and stability and 

control

` Increases the commercialization 

potential for sub/super/hypersonic 

modules and other associated 

products

Firm Contact

M4 Engineering 

Katherine Alston

kalston@m4-engineering.com

4020 Long Beach Blvd 

Long Beach, CA 90807–2617

Phone: 562–981–7797

Proposal Number: 08-2: A2.08-8438

NASA/TM—2014-218497 19
Blade Vibration 

Measurement System 

For characterization of closely spaced modes and mistuning

The Phase I project successfully demonstrated that an advanced 

noncontacting stress measurement system (NSMS) could improve 

classification of blade vibration response in terms of mistuning and closely 

spaced modes. The Phase II work confirmed the microwave sensor design 

process, modified the sensor so it is compatible as an upgrade to existing 

NSMS, and improved and finalized the NSMS software. The result will be 

stand-alone radar/tip timing radar signal conditioning for current conventional NSMS users (as an upgrade) and new users. The hybrid system will 

use frequency data and relative mode vibration levels from the radar sensor 

to provide substantially superior capabilities over current blade-vibration 

measurement technology. This frequency data, coupled with a reduced number 

of tip timing probes, will result in a system capable of detecting complex blade 

vibrations that would confound traditional NSMS systems. 

The hardware and software package was validated on a compressor rig at 

Mechanical Solutions, Inc. (MSI). Finally, the hybrid radar/tip timing NSMS 

software package and associated sensor hardware will be installed for use in 

the NASA Glenn spin pit test facility.

Applications

NASA 

` Gas turbine propulsion engines

` Turbomachinery for liquid 

propulsion engines

` Steam turbines for power 

generation

Commercial

` Aircraft engines

` Industrial gas turbines

` Steam turbines in power 

generation and/or oil and gas

` Predictive health management 

for aerospace and industrial 

machines

Phase II Objectives

` Develop and demonstrate 

improvements in sensors and 

data acquisition

` Validate prototype work using 

instrumented compressor rig

` Characterize mistuning, mode 

shapes, and frequencies in 

test article

` Develop prototype software

` Perform rig tests, with synchronous 

and nonsynchronous blade 

excitation

` Compare strain gage data to 

noncontacting measurements

)LULÄ[Z

` Improves blade vibration 

measurement capability 

` Reduces cost and risk of 

developing and operating gas 

turbine engines

Firm Contact

Mechanical Solutions, Inc.

Michael J. Platt

mjp@mechsol.com

11 Apollo Drive

Whippany, NJ 07981–1423

Phone: 973–326–9920

Proposal Number: 07-2: A2.04-8395

NASA/TM—2014-218497 20
Fully Integral, Flexible 

Composite Driveshaft 

All-composite driveshaft technology for improved 

performance

An all-composite driveshaft incorporating integral flexible diaphragms was 

developed for prime contractor testing. This new approach makes obsolete the 

split lines required to attach metallic flex elements and either metallic or 

composite spacing tubes in current solutions. Subcritical driveshaft weights can 

be achieved that are half that of incumbent technology for typical rotary wing 

shaft lengths. Spacing tubes compose an integral part of the initial tooling but 

remain part of the finished shaft and control natural frequencies and torsional 

stability. A concurrently engineered manufacturing process and design for 

performance competes with incumbent solutions at significantly lower weight 

and with the probability of improved damage tolerance and fatigue life. 

Applications

USNavy photo

NASA 

` Rotary wings: 

t Tail rotor drives

t Tilt-rotor crossover drives

t Tandem rotor connection

shafts

Commercial/Military

` Rotary wing programs

` Weight-sensitive driveshaft 

applications

t Joint Strike Fighter (JSF)

lift fan flexible shafts

t Navy hovercraft/air cushion

landing craft

` Industrial applications

t Very high speed

turbomachinery that relies 

on long titanium spacing 

tubes

Phase II Objectives

` Build tooling and prototypes for 

larger diameter applications

` Build prototypes for JSF, hovercraft, 

tandem rotor helicopters

` Produce additional test articles for 

prime contractor fatigue test and 

support qualification plan

)LULÄ[Z

` Improves driveshaft torque 

` Provides higher operational speed

` Improves fatigue performance 

(resistance and damage tolerance)

` Reduces part count and weight

Firm Contact

Lawrie Technology, Inc.

Duncan Lawrie

duncan@lawrietechnology.com

227 Hathaway E

Girard, PA 16417–1552

Phone: 814–746–4125

Proposal Number: 07-2: A2.10-8919

NASA/TM—2014-218497 21
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01-11-2014

2. REPORT TYPE

Technical Memorandum

3. DATES COVERED (From - To)

4. TITLE AND SUBTITLE

An Overview of SBIR Phase 2 Airbreathing Propulsion Technologies

5a. CONTRACT NUMBER

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6. AUTHOR(S)

Nguyen, Hung, D.; Steele, Gynelle, C.; Bitler, Dean, W.

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WBS 471296.01.03.01

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National Aeronautics and Space Administration

John H. Glenn Research Center at Lewis Field

Cleveland, Ohio 44135-3191

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E-18981

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NASA

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Subject Category: 01

Available electronically at http://www.sti.nasa.gov

This publication is available from the NASA Center for AeroSpace Information, 443-757-5802

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14. ABSTRACT

Technological innovation is the overall focus of NASA’s Small Business Innovation Research (SBIR) program. The program invests in the

development of innovative concepts and technologies to help NASA’s mission directorates address critical research and development needs

for agency projects. This report highlights innovative SBIR Phase II projects from 2007-2012 specifically addressing areas in Airbreathing

Propulsion which is one of six core competencies at NASA Glenn Research Center. There are twenty technologies featured with emphasis

on a wide spectrum of applications such as with a Turbo-Brayton cryocooler for aircraft superconducting systems, braided composite

rotorcraft structures, engine air brake, combustion control valve, flexible composite driveshaft, and much more. Each article in this booklet

describes an innovation, technical objective, and highlights NASA commercial and industrial applications. This report serves as an

opportunity for NASA personnel including engineers, researchers, and program managers to learn of NASA SBIR’s capabilities that might

be crosscutting into this technology area. As the result, it would cause collaborations and partnerships between the small companies and

NASA Programs and Projects resulting in benefit to both SBIR companies and NASA.

15. SUBJECT TERMS

Turboelectronic aircraft; Cryocooler; Rotorcraft; Composite structure; Hybrid gear; Engine air brake

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