Aircraft Engine Advanced Controls Research under … · at Lewis Field Glenn Research Center...

at Lewis Field

Glenn Research CenterIntelligent Control and Autonomy Branch

Aircraft Engine Advanced Controls Research under

NASA Aeronautics Research Mission Programs

Dr. Sanjay Garg

Chief, Intelligent Control and Autonomy Branch

Ph: (216) 433-2685

FAX: (216) 433-8990

email: [email protected]://www.grc.nasa.gov/WWW/cdtb

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Aeronautics Research Mission Directorate

Advanced Air

Transport TechnologyAATT - (GRC)

Advanced Air

Vehicles (AAVP)

Airspace Operations

And Safety (AOSP)

Integrated Aviation

Systems (IASP)

NASA Aeronautics Program StructureEffective FY15

Transformative Aeronautics

Concept (TACP)

Revolutionary Vertical

Lift TechnologyRVLT - (LaRC)

Commercial Supersonic

TechnologyCST - (LaRC)

Advanced CompositesAC - (LaRC)

Aeronautics Evaluation

and Test CapabilitiesAETC - (ARMD)

Airspace Technology

DemonstrationATD - (ARC)

SMART NAS – Testbed

for Safe Trajectory

Operations (ARC)

Safe Autonomous

System OperationsSASO - (ARC)

Environmentally

Responsive

AviationERA - (LaRC)

UAS Integration

in the NAS(AFRC)

Flight Demonstration

and CapabilitiesFDC - (AFRC)

Cross Program

OperationsCPO - (ARMD)

Leading Edge

Aeronautics Research

for NASALEARN - (ARMD)

Transformational Tools

and TechnologiesTTT – (GRC)

Convergent Aeronautics

SolutionsCAS - (ARMD)

--------------------- Mission Programs ------------------- Seedling Program

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at Lewis Field


Advanced Air Vehicles Program

• AAVP – Intelligent Propulsion System Architecture

• AATT – Dynamic Systems Analysis Tools and Methods

• AATT – Engine Icing Detection and Mitigation

• AATT – Active Turbine Tip Clearance Control

• CST – Aero-Propulso-Servo-Elasticity

• AETC (HTP/AFRL) – CCE-LIMX Modeling and Control

Airspace Operations and Safety Program

• ATD – Propulsion Simulation for Enhanced Simulator Fidelity

• SMART NAS – Runtime Assurance of Complex Systems

Transformative Aeronautics Concept

• TTT – Distributed Engine Control Tools and Technologies

• TTT – Model Based Engine Control

• TTT – T-MATS Tool Development

• TTT – Active Combustion Control

• TTT – Pressure Gain Combustion

Other

• VIPR3 – Gas Path Fault Diagnostics

GRC “Aero Controls” Tasks

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Potential Growth Areas

& current GRC Controls Work

AAVP/AATT• Technologies for increased efficiency and reduced emissions for commercial

passenger aircraft – including small core / compact gas turbine• Model Based Engine Control• Active Combustion Control• Active Turbine Tip Clearance Control

• Hybrid Electric Propulsion for single aisle commercial passenger aircraft• eTC (emerging Technical Challenge): DRAFT: “Turbine/Generator Integration & Controls: Design and test a gas generator compatible with HGEP system which maintains performance and operability with a varying (25% - 100%) electric load”

TAC/Autonomous Systems (Project being formulated in FY17)• Technologies to enable safe autonomous operation of air vehicles (no human in the

direct control loop)• Intelligent Propulsion System Architecture (funded through AAVP in FY16)

TAC/CAS, AAVP/RVLT• Enable a broad expansion of UAVs – new missions, improved efficiency and flight

time, reduced emissions and noise

at Lewis Field


OverviewMBEC is a significant control logic architecture technology advancement that will help realize the goals of efficiency improvements by considering controls in the design process. This technology will increase the design space available for operation due to the tighter control of margins and allow for design studies to increase efficiency

Model Based Engine Control (MBEC)P

ress

ure

Rati

o

Corrected Mass Flow

OpLine

Stall Line

Stall Margin

ConstraintLeft: Compressor performance map illustrating potential reduction in margin. Right: MBEC implementation illustrating tight control of SM and thrust to enable thrust specific fuel consumption improvements

Approach• Define the conservative margin in baseline design• Implement MBEC for a tighter control reducing

uncertainty and transient margins• Redesign engine with reduced margin and ensure safe

operation• Work with engine designers to realize efficiency

improvement

at Lewis Field

Glenn Research Center

JASC Device Drive Electronics Jansen Aircraft Systems

Controls, Inc. (JASC)SBIR Phase II

Fuel-Flow Modulator

Active Combustion Control - Fuel Modulator Development

WASK Engineering, Inc.SBIR Phase I

Prototype Model Fuel-Flow Modulator

Georgia TechFuel-Flow Modulator

Active Signal Technologies, Inc.,

Fuel-Flow Modulator

Intelligent Control and Autonomy Branch

Phase Shift

Controller

Fuel

Valve

Fuel lines, Injector

& Combustion

AcousticsNL

Flame

White Noise

++

+

Filter

Pressure from

Fuel Modulation Combustor Pressure

Instability Pressure

High Bandwidth fuel flow modulation is essential for suppression of thermo-acoustic instabilities

at Lewis Field


Active Turbine Tip Clearance Control (ATTCC)Goal:

• Maintain tight control of clearance between the turbine blade and its casing structure by means of a fast response actuator – reduce the clearance needed in steady-state

Approach: • Develop a generic physics-based dynamic model to predict the turbine tip clearance in the high

pressure turbine (HPT) during transients• Integrate tip clearance model with an engine dynamic simulation and conduct sensitivity analyses to

quantify the relationship between actuator performance and engine efficiency gains


• Generic tip clearance model incorporating case cooling flow integrated with the C-MAPSS40k engine simulation

• Predicted tip clearance is representative of the typical “pinch” point during transients

Performance impact at cruise while varying the temperature of the cooling flow

at Lewis Field


Tool for Dynamic Modeling and Analysis of HEP Hardware &

Control Architectures


Overall System – throttle to

thrust response

- Control of Turbomachinery +

PMAD + Propulsor Control to

meet FAA dynamic

performance requirements

- Modeling of subsystem

interactions

Propulsion

Control Architecture

Feasibility

Analysis

Turbine Generator PMAD

Battery PowerConditioning

Motor

Fan

Hardware

Architecture

Feasibility Analysis

ThrottleThrust

• Collaboratively develop the basic subsystem models and interfaces required for an HEP system simulation with sufficient fidelity to perform subsystem hardware requirements and control architecture studies to meet overall system (throttle command to thrust response) dynamic performance requirements and operational life/safety requirements

at Lewis Field


Intelligent Propulsion System ArchitectureTo Enable More Autonomous Vehicle Operation


Goals/Objectives: Develop an engine control architecture that works harmoniously with the flight control, with reduced pilot intervention over time.• Automatically recognize the vehicle operating

mode and configure the engine control scheme to provide optimal performance for that mode with knowledge of the engine condition and capability.

• Preliminary simulation based demonstration will be done for specific elements of the architecture and technology gaps will be identified to achieve overall

desired capability.Progress: Preliminary architecturehas been developed building upon previous engine control and diagnostics research. Specific demonstration cases are being readied using TCM/C-MAPSS40k simulation.

National Aeronautics and Space Administration

www.nasa.gov

Small UAV Propulsion – Overview

Example small UAV civil

applications

• Inspection

• Photography and filming

• Spraying

• Mapping

• Weather

• Surveillance

• Delivery

• MedEvac

• Low cost flight demonstrators

NASA ARMD Vision

• The skies will accommodate thousands of times the

number of vehicles flying today

• There will be a radical increase in new and cost-

effective uses of aviation

• Autonomy will enable new types of vehicles and

missions, unconstrained by the requirements of

today’s conventional vehicles

NASA ARMD Strategy

• Enable a broad expansion of UAV applications

• Improve current configuration cost, speed, payload,

safety, and noise

• Open new markets with new configurations and

capability

Workshop Focus

• Small UAV propulsion systems in the 200 to 2,000 lbs

thrust category

• Gas turbine-based UAV propulsion systems only

o Includes turbofan, turbo-shaft, turbojet, and hybrid

electric propulsion

o Does not include battery or piston-based propulsion

at Lewis Field


Break-Out Sessions

• Discuss propulsion control technology development needs for:

10:00President’s Room: Turbomachinery Efficiency/Emission – Joe Connolly/Dennis Culley, Board Room: Small UAV propulsion – Don Simon1:00President’s Room: Hybrid Electric Propulsion – George Kopasakis/Joe ConnollyBoard Room: Autonomy – Jonathan Litt

• Expected Outcome:For each topic area, identify Top 2-5 Control Technology Challenges to meet the goals

For each Control Technology Challenge:

• Brief Description (what we are trying to do and why)

• Relevance to Goals

• What is the benefit – quantitative/qualitative

• Technology Development Focus and Timeframe – 5-10, 10-20, >20 years

at Lewis Field


Break-Out Sessions - Process

• Brief Presentation by Session Lead• Link Topic Area to Thrust(s) and Goals• Link to relevant Roadmap• Summary of current relevant work and/or plans

• Listing of potential control technology challenges to meet the Goals

• Identification of up to 5 top control technology challenges

• Discussion to complete the report out information for each identified technology area

• During the breaks, Session Leads will prepare the Report Out presentation

Questions?

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Next Steps

• The presentations from today including the Breakout Session Reports will be made

available on the Branch website

• Link to presentations and feedback forms will be e-mailed to the attendees

• Please be sure to return the completed feedback and any additional comments

on the breakout session reports

In the next few months:

• For each topic area, using the information from the breakout session discussions,

draft roadmaps will be developed in consultation with project folks – format on

next chart

• Draft roadmap document will be shared with the attendees and feedback requested

• A paper documenting the roadmaps will be written for a future conference – either

Turbo Expo or JPC to provide an opportunity to share with broader community

• The Roadmap document will be shared with Aero project management team and

appropriate portions used to build advocacy in specific projects for future work

at Lewis Field


Technology Challenge X – Draft Roadmap Format

• Brief Description (what we are trying to do and why)

• Relevance to Goals

• What is the benefit – quantitative/qualitative

• Technology Development Focus and Timeframe – 5-10, 10-20, >20 years

• High Level Deliverable (in the expected time frame, eg. demonstrate technology at TRL ? on aircraft/engine/lab ….)

• Intermediate Deliverables

• Advancements needed in other disciplines to achieve high level deliverables (Discipline, Technology Need)

• Potential Collaboration outside NASA

• Level of Challenge (difficulty of achieving high level goal with “reasonable” resources) – High, Medium, Low

• Level of Resources Needed – High (>$10M), Medium (<$10M > $2M) Low (<$2M)

• Mapping to most appropriate Program/Project – relevance to program/project plans

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