Dan Frias HONEYWELL CLEEN II 05/07/2019 Consortium Presentation – Open Discussion

UNLIMITED RIGHTS Agreement Number: DTFAWA-15-A-80017 Contractor Name: Honeywell International Inc. Address: 111 S. 34th Street Phoenix, Arizona 85072-2181 21-15790(07)-2 1 Agenda

• Elevator Speech • Honeywell’s Products and CLEEN II • CLEEN II Technologies • Technology Maturation Approach and Program Schedule • Engine and Aircraft Systems Analysis Status • Technologies Status – Compact Combustor • Technologies Status – Blade Outer Air Seal (BOAS) • Future Plans • Summary

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 2 CLEEN II Elevator Speech • Honeywell’s CLEEN II program is maturing advanced turbine and combustor technologies to reduce weight for improved fuel burn and reduced emissions

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 3 Next Generation Turbofan Can Benefit from CLEEN Technologies to Reduce Fuel Burn and Emissions

HTF7000 Series • State-of-the-art (SOA) performance Engine Platform • Industry leading dispatch reliability HTF7000 Bombardier Challenger 300 • Quantum leap in value: cost and durability HTF7350B Bombardier Challenger 350 • Versatile technology: 7000-10000 lbs thrust HTF7250G Gulfstream G280 • Five aircraft applications to date - > 1000 engines in service HTF7500E Embraer Legacy 450/500 - > 2 million flight hours HTF7700L Cessna Citation Longitude

CLEEN Technologies Enhance Future Product Capabilities

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 4 Honeywell CLEEN II Technologies

• Under CLEEN II Honeywell is developing and demonstrating advanced Combustor and Turbine technologies

Blade Outer Air Seal The advanced Turbine BOAS increases high pressure turbine efficiency, resulting in reduced fuel burn.

Compact Low Emissions Combustor integrates

RICH advanced aerodynamics and QUENCH LEAN fuel injection technologies to reduce engine NO emissions Compact X Combustor and weight, contributing to reducing fuel burn.

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 5 CLEEN II Technology Summary

CLEEN Goal Technology Benefits, Applications and Collateral Benefits Impact Name Compact Emissions • Goal - Reduce NOx emissions to >50% margin (CAEP/8), Combustor for next generation super mid-sized class business jet System turbofan engines for 2025 entry into service (EIS) Advanced Fuel Burn • Goal - Enable turbofan engine fuel burn reduction >22% Turbine BOAS relative to the baseline engine for next generation turbofan, System turboshaft, turboprop engines for 2025 EIS

Compact Collateral Benefits Combustor • FAA CLEEN programs support validation of Low-k thermal barrier coating (TBC) and Alloy 10 powder metal super-alloy • Currently being evaluated by major aerospace and industrial engine original equipment manufacturer (OEMs) • Applied to current and future turbine propulsion and industrial engines should increase fuel efficiency and lower operating costs

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 6 CLEEN II Value and Opportunity Cost

Technology CLEEN II Value Opportunity Cost (If FAA had not funded…) Fuel Burn Enables >22% fuel burn Likely delays technology development improvement over baseline engine and implementation of advanced fuel through an advanced engine burn technologies impacting near term architecture with high efficiency reductions in fuel burn and CO2 turbine technologies emissions.

Emissions Enables > 2x improvement in NOx Achieving ultra-low emissions is very margin over Honeywell SOA challenging and requires major combustor through integration of investment. advanced combustor aerodynamics, Without FAA support, level of internal fuel placement and materials investment reduced and level of current customer/regulatory requirements, will result in delayed implementation of ultra low emissions technologies.

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 7 Technology Maturation Approach

TRL 3 TRL 4 TRL 5 TRL 6

RICH

QUENCH LEAN

Analysis and Technology Component / System Engine Demonstration Testing Development Testing Demonstration and Validation Testing

May 2019 Status

Progressive Approach to Validate Technology and Reduce Risk

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 8 Progress and Achievements

• Systems Engineering - Engine detailed design review (DDR) complete - Gulfstream assessment complete - Provide assessment information to Georgia Tech upon test completion • BOAS Development - Coupon material characterization testing complete - Structural test of engine attachment design complete - Thermal characterization test complete - Shroud engine hardware inspection complete (Engine Test Q3 2019) - Air plasma spray (APS) TBC process down-select complete • Combustor Development - Initial rig testing complete - Second Phoenix rig test underway (Q2 2019) - Preliminary NASA rig design nearing completion

Next Steps to Validate Technology Designs

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 9 2019 Program Schedule

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 10 2020 Program Schedule

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 11

Engine and Aircraft Systems Analysis Status

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 12 Systems Progress and Achievements

• DDR Complete - Engine system architecture and cycle defined - Reference aircraft and engine analysis complete - >22% aircraft mission fuel burn reduction over baseline engine achieved with CLEEN II and Honeywell technologies - Ground engine test configuration layout complete - Linkage with Honeywell’s marketing plans for near- and long-term potential platforms complete

Next Steps to Refine and Validate Technology Designs

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 13 CLEEN II Aircraft Fuel Benefits • CLEEN II aircraft mission fuel burn reduction goal of 22% from baseline engine • Fuel burn reduction includes CLEEN and Honeywell technologies

CLEEN I Technologies CLEEN II 5.0% Technologies Fuel Burn 2.1% Benefit Fuel Burn Benefit

CLEEN II Continues to Contribute to Fuel Burn Reduction

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 14

Engine and Aircraft Benefits Systems Analysis • Improved power-to-weight ratio • Reduced engine thrust specific fuel consumption (TSFC) • Reduced fuel burn and NOx emissions

Risks/Mitigations • Insufficient aircraft fuel burn assessment/work with Gulfstream and Georgia Tech

Objectives Accomplishments/Milestones • Define a ‘CLEEN II’ engine with • Engine DDR complete advanced technologies that enable • Gulfstream assessment complete reduction in fuel burn and NOx emissions Technology Schedule Work Statement • Perform engine preliminary and detail Task 1 - PDR engine concept reviews along with

independent assessments of the Task 2 - DDR technology benefits

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 15

CLEEN II Technologies Status Compact Combustor

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 16 Compact Combustor Technology

Compact Combustor Attributes • Improved aerodynamic design • Advanced cooling and materials • Improved durability enabling higher temperature cycle to reduce fuel burn • Reduced weight

Compact Combustor is an advanced combustor design that integrates SOA aerodynamic design, advanced material selection and coatings and

RICH improved fuel control. QUENCH LEAN

Combustor Technology to Reduce NOx to >50% Margin to CAEP/8

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 17 Compact Combustor Accomplishments

• Combustor technology demonstration testing progressing to enable refinements to combustor system to meet program goals - Evaluated multiple fuel injector and combustor aerodynamic design configurations designed using advanced computational fluid dynamics (CFD) large eddy simulation (LES) analysis to optimize performance, emissions and wall cooling

• Currently rig testing latest CLEEN II combustor in Phoenix Combustor Test Laboratory with results expected in June

• Completed design review with NASA and FAA of CLEEN II annular combustor rig to be tested in the NASA Glenn Advanced Subsonic Combustor Rig (ASCR) facility in mid-2020

Combustor Technology Progressing to TRL 4 in Q2 2019

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 18 Compact Combustor Next Steps

• Continue technology demonstration and annular combustor system development rig testing through Q4 2019 • Complete fabrication and build NASA rig (adaptive rig hardware) to support validation testing at NASA ASCR test facility in Q2 2020 to: Honeywell Rig Testing - Validate combustor NOx emissions and performance - Measure combustor nvPM - Validate Liner wall temperatures for durability assessment • Complete Honeywell engine validation testing in Q3 2020 Honeywell Engine Testing Technology Maturation Plan to Demonstrate TRL 6

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 19 Combustor System Technology Benefits • Lower engine emissions • Reduction in fuel burn Risks/Mitigations • Operability - Rig test validation at altitude cond. • Emissions - Test validation at full engine cycle

RICH

QUENCH LEAN operating conditions in NASA facility • Combustor Durability - Demo engine cyclic test

Objectives Accomplishments/Milestones • Completed initial Compact Combustor design • Reduce NOx emissions • Rig testing annular combustor technologies and • Reduce combustor weight full system to demonstrate program goals • Completed design of CLEEN-II NASA combustor rig. Testing planned in ASCR facility in 2020 Work Statement Technology Schedule • Develop and demonstrate a low emission compact combustor for improved NOx and fuel burn in a an engine

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 20

CLEEN II Technologies Status Blade Outer Air Seal (BOAS)

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 21 Blade Outer Air Seal (BOAS) Technology

BOAS Attributes • Increased Temperature Capability • Reduced Leakage • Effective Tip Clearance • Improved Durability • Reduced Weight

Blade Outer Air Seal is an advanced turbine system design that addresses blade-to- shroud interaction, high temperature capability and durability.

BOAS Technology to Reduce Turbofan Engine Fuel Burn 2.1%

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 22 Honeywell’s Next Gen APS TBC Technology

Low-k APS TBC Attributes • 15-20% lower conductivity • 10-20% improved erosion rate • Equivalent spallation life • Phase stable above 3,000°F • Ready to test, 2019

Lower Thermal Conductivity TBC is a protective ceramic coating applied to the external surface of engine components for insulation and to inhibit oxidation and hot corrosion.

Air Plasma Spray Technology Progressing to TRL 4 in Q3 2019

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 23 Advanced BOAS System Accomplishments

• Turbine Blade/Shroud - Advanced blade material oxidation characterization complete - Advanced blade/shroud rub testing well underway - Engine shroud design complete and hardware received - Shroud material mechanical testing complete - Shroud material thermal characterization testing complete

• APS Low-k TBC - Identified most promising powder and processing route for APS Low-k TBC - Initial thermal conductivity testing complete - Thermal phase stability testing complete

BOAS to Achieve System TRL 4 in Q3 2019

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 24 Advanced Turbine BOAS System Technology Benefits • Fuel burn reduction • Improved power-to-weight ratio Low Thermal Conductivity TBC Risks/Mitigations • Insufficient material durability/rig and engine test Blade Outer Air Seal • Insufficient performance/alternate BOAS design Objectives Accomplishments/Milestones • Improve high pressure turbine (HPT) • HPT shroud design complete and hardware efficiency received for 2019 development engine testing • APS Low-k TBC processing down-selected and shows good results Work Statement Project Schedule • Develop and demonstrate a BOAS system that improves HPT efficiency in an engine

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 25

Technology Readiness Level (TRL) Maturation and Summary

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 26 Future Plans – TRL Maturation

• TRL 4 – 2019 - Blade Tip Mechanical Testing – Q2 2019 - Annular Compact Combustor Testing – Q2 2019 - APS Low-k TBC Process Optimization – Q3 2019

• TRL 5 – 2019-2020 - Development Test(1) – Q3 2019 . HPT Shroud Technology Assessment - Development Test(2) – Q1 2020 . HPT BOAS Technology assessment

• TRL 6 – 2020 - NASA Combustor System Testing – Q2 2020 - Endurance Engine Test – Q3 2020 . Engine emissions assessment . Endurance engine test to support TRL 6 validation of Compact Combustor and BOAS Technologies

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 27 Summary • Honeywell CLEEN II program is progressing well to mature the compact combustor and the advanced turbine BOAS to reduce fuel burn and NOx emissions

- Engines and Aircraft Systems Analysis . Engine DDR complete . Gulfstream aircraft/engine assessment complete - Compact Combustor . Initial compact combustor design complete . Rig testing annular combustor technologies and full system to demonstrate program goals well underway . Completed design of CLEEN II NASA combustor rig. Testing planned in ASCR facility in 2020 - Turbine BOAS . HPT shroud design complete and hardware received for 2019/2020 development engine testing . APS Low-k TBC processing down-selected and shows good results

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover. 28

21-15790(07)-2 Use or disclosure of information contained on this page is subject to the restrictions on the cover.