Ramgen Technologies

1 0900-01088 UW Presentation Compression Technology Path

RampressorTM Ramgen Turbine Ramgen Engine

• Increased Efficiency • RampressorTM Integrated • Supersonic Compression And Compression Technology With Conventional On-Rotor Combustion/Power • Aerodynamic and Combustor & Turbine Extraction Technology Mechanical Designs At ~3:1 • Cycle Efficiency Increased • High Overall Cycle Efficiency: to ~9:1 Pressure Ratios Due to RampressorTM High Compression and Power • RampressorTM-Specific Efficiency Extraction Efficiencies Component Layout & Cost • Higher Pressure Ratio Designs (>9:1)

2 0900-01088 UW Presentation Compression/Power Technology Applications

• Air Compressors • Turbochargers RampressorTM • Turbines • Industrial Processes • Refrigeration • Gas Pipeline Boosters

• Base Load Power Rampressor Generation Turbine • Hybrid Fuel Cell • Waste Fuel Utilization

• Base Load Power Ramgen Engine Generation • Expanded Waste Fuel Utilization 3 0900-01088 UW Presentation Conceptual Rendering - Engine

4 0900-01088 UW Presentation 2.8 MW Engine Design Review

• Two-day all government design review at NASA-Glenn (April, 2002) • NETL, Oak Ridge, NASA, AFRL, Army Research Lab • Facilitated by third party, Parsons Group • Followed the “technology readiness level” approach

Recommendation: Move forward but develop subsystems separately before full engine integration

Shock Wave Advanced Compression Combustion

5 0900-01088 UW Presentation Various Flight Inlet Types For Propulsion

6 0900-01088 UW Presentation Typical Supersonic Inlet Pressure Recoveries

~93%

~93% Inlet Pressure Recovery Typical @ M = 2 A Well Designed Inlet Can Do A Little Better Than MIL-SPEC

7 0900-01088 UW Presentation Supersonic Compression vs. Relative Mach #

20 Sp. Heat Ratio = 1.4 18 Sp. Heat Ratio = 1.3 16 o i t

a 14 e R r 12 essu r 10 ~9.89:1

c P Pressure Ratio i t

a 8 t S / al

t 6 o T 4

2

0 0.0 0.5 1.0 1.5 2.0 2.5 3.0 Relative Mach Number

Pressure Ratio Non-Linear With Relative Mach # Supersonic Inlets Produce Significant Compression

8 0900-01088 UW Presentation Typical Supersonic Inlet: F-15

9 0900-01088 UW Presentation Rampressor Rotor Design

Mrel = ~2 M = ~0.3 - 0.5 Supersonic F-15 Inlet

Rampressor = ~2 Mrel M = ~0.5 Rotor

10 0900-01088 UW Presentation Typical Rotating Supersonic Flow Path

Subsonic Diffuser • Rotor Flow Path: Compression – 3 Supersonic Ramp Compression Inlet Flow Paths On Disk Rim – High Efficiency,

“Pre-Inlet” Compact Compression Flow Surface – Minimal Number of Leading Edges

Strake • Combination of Wall Supersonic Flight Inlet & Conventional Axial Flow Compressor Aerodynamics

11 0900-01088 UW Presentation Gas Turbine Tech. Insertion Opportunity

Gas Turbine with Multi-stage Axial Compressor

Replace or “De-stage” Gas Turbine Compressors with a Single Stage High Pressure Ratio Rampressor

Rampressor Rotor

12 0900-01088 UW Presentation Replace or “De-Stage” Conventional Compressors

3-Stage Intercooled Compressor Package Single-Stage Rampressor

Replace stages with Rampressor Rotor

Replace with Rampressor

• Simple single-stage design • High speed direct drive • Magnetic bearings • Useable heat recovery • Eliminates: • 2nd & 3rd stage(s) • Speed increaser gearbox • Intercooler(s) • Lube oil system

13 0900-01088 UW Presentation RampressorTM Demonstration Program

• Goals: Test Rig Assembly – Demonstrate Rampressor Rotor Operation • Supersonic Compression – Characterize Rotor Efficiency • How: – Design & Build Rotor Test Apparatus – Conventional Compressor Test Rig Design – Characterize Rotor-Only Efficiencies • Where: – Boeing Nozzle Test Facility (NTF) – Boeing Field, Seattle • When – Installation April ‘03 – Testing To Start August ‘03 – Through 1st Quarter of CY04

Boeing Test Cell Rotor

14 0900-01088 UW Presentation Rampressor 1 Preliminary Test Results

Rampressor 1 Test Rig Flow Path (Rotor-Only) Efficiency vs. Rotor Pressure Ratio Design Intent, Perf. Code PR Match, & Rig Data 1.00 0.90 0.80 0.70 0.60 0.50 0.40 Efficiency 0.30 Perf. Code Match To PR

Adiabatic Rotor-Only Adiabatic Rotor-Only 0.20 Rig Data 0.10 Design Intent 0.00 1.0 1.5 2.0 2.5 3.0 3.5 4.0 Rotor Pressure Ratio Test Rig Data Matching Well With Predictions

15 0900-01088 UW Presentation Rampressor 1 Test Rig Status

• Achieved Full Rotor Speed – Mechanical Systems Now Working Adequately – Achieved Design Rotor-relative Mach Number (M = 1.6) • Started All 3 Rotor Inlets – Have Not Experienced Instabilities, Surge, Or Inlet-to-inlet Variations – Benign Surge Characteristics => Very Good Thing • Near Design Pressure Ratio/Mass Flow Point – Operating As A Compressor! – Working To Increase Rotor Efficiency & Pressure Ratio • Have Not Optimized All Available “Knobs” To Increase Pressure Ratio, Mass Flow, and Efficiency – Rotor Geometry, Tip/Case Clearance, Bleed Amounts And Locations, RPM, Etc.: Additional Rotor Available For Changes/Upgrades/Etc.

• Overall Operation of Rotor Aerodynamics Is As Designed/Intended – Analytical/Numerical Design Tools Have Basic Validation: Validation Continuing With Test Data Generation

16 0900-01088 UW Presentation Rotating Ramjet Flowpath

(with combusion)

Rotating Ramjet Flowpaths On Rim of High Speed Disc

0900-00035-0002 Rev B 0900-00222-0002, 0900-00004 Rev C 17 0900-01088 UW Presentation Engine Rotor

• Ramjet Power = Thrust x Lever Arm x Rotation Rate x No. Ramjets

Ramjet Thrust Vector

Axis of Rotation

Lever Arm (Distance from Axis of Rotation to Line of Action of Thrust Vector)

Dimensional Example: lbf x ft x rad/s x # Jets = ft-lbf/sec

0900-00761 0900-00568 18 0900-01088 UW Presentation Combustor Details

Nozzle Combustor Side Walls Outflow

Pilot Fuel

Center Body

Supplemental Fuel

Dump Plane Cold Inflow

0900-00753 0900-00568 19 0900-01088 UW Presentation Conventional Swirl-Stabilized Combustor

• Most Gas Turbine Combustors and Industrial Burners • Flame Stability is Dependent on Main Flow

Swirling Flame

In-Flow Air Combustion Zone

Flame is Unstable at Reduced Temperatures

20 0900-01088 UW Presentation Advanced or “Trapped” Vortex Combustion ?

• No Swirl Vanes Required For Flame Stability • Main Vortex is Stationary in a Controlled Cavity

In-Flow Air Combustion Zone

Main Vortex

Conceptual Rendering

Combustion is Stabilized by Controlling the Fluid Dynamics

21 0900-01088 UW Presentation Advanced Vortex Combustor (AVC)

• AVC has seen wide exposure at WPAFB and DOE NETL • GE, Williams Engines and others are pursuing commercial applications • Ramgen, DOE and CEC are teamed to develop low NOx design

• Flame is Independent of Main Flow for Greater Stability • Greater Combustor Turndown • Potential to Achieve Very Low Single Digits NOx

In-Flow Air Combustion Zone

Trapped Vortex Cavity

22 0900-01088 UW Presentation NOx for Industrial Ground-Based Combustion Turbines

Leonard and Stegmaier (1994) Curve Fit

) 100 2 O 1990’s (Prior To DOE ATS Program) 15%

@ Existing State-Of-The-Art v 10

ppm Target: 3 ppm ( x O N 1 1600 1700 1800 1900 2000 2100 Flame Temperature (K) Lower Flame Temperature: • Lower NOx emissions • More Unstable Combustion 23 0900-01088 UW Presentation Phase I AVC Proof-of-Concept Natural Gas Burning Demonstration

Phase I Best Result Single Digits NOx, AVC Combustor CO, and UHCs

Phase II Goal 3 ppm NOx

Ramgen is First to Demonstrate Single Digit NOx with AVC

24 0900-01088 UW Presentation AVC Gas Turbine Demonstration

AVC Retrofit

Example: Demonstrate 3ppm NOx Without Expensive Xonon Catalyst

Kawasaki 1.4MW Gas Turbine 25 0900-01088 UW Presentation Compression Product Development

• Single Stage, Low PR Gas Compression • Single Stage, ~10:1 • High Efficiency Gas • Hybrid Fuel Cell- Industrial Gas Turbine Based On Turbine Compression Rampressor Compressor

Rampressor Rampressor Rampressor Ramgen 1/1.6S II Turbine Engine 2.5:1 - 4:1 9.9:1 Integrated Full Ramjet Pressure Ratio Pressure Ratio Rampressor/Turbine Technology ~3,000 CFM ~1,500 CFM ~250 kW On Rotor Proof-of-Concept Tech. Demonstrator Integration Demonstration

26 0900-01088 UW Presentation