TriJet Propulsion for Reusable Hypersonic Vehicles Dr. Adam Siebenhaar Director Aerojet Hypersonic Propulsion Phone: 916-355-2535 adam.siebenhaar@aerojet.com Released For the Public
Robust Operation Requirements For Turbine Based Combined Cycle Vehicle Subsonic (Mach 0 to 1) Self Ferry Runway Take-Off In-flight Tanking Powered Landing/Go Around Capability Super & Hypersonic Operation (Mach 1 to 6) Substantial Positive Thrust Margin Especially During Transonic Flight & Combined Cycle Engine Mode Transition(s) Released For the Public
Current Major Combined Cycle Propulsion Issues Normalized Vehicle Drag (Drag/Drag max ) & Thrust (Thrust/Drag max ) 1.2 Vehicle Drag Insufficient TE-Thrust Net Transonic Thrust 1.0 DMRJ-Thrust Lack of Full Scale 0.8 TE – DMRJ Ground Test Thrust Gap Facilities 0.6 DMRJ Thermal 0.4 Management 0.2 0.0 0.0 1.0 2.0 3.0 4.0 5.0 6.0 7.0 Flight Mach Number Released For the Public
Released For the Public Aerojet TriJet Concept Operation Front Views Vertical Cut Variable Geometry Doors Inlet Capture Area Port Mach 2.5 TE (Available Now) Engine Mach ~4+ Ejector Ramjet Mach 3.5 -7 Dual Mode Ramjet ACCII Wind Tunnel Test Model DMRJ DMRJ Vertical Cut Mach Range Door Settings (No Doors in DMRJ Flowpath) Comment Turbine Engine Ejector Ramjet Engine Inlet Exit Inlet Exit 0 to 1+ Open Open Open Open 1+ to 2.5 Partial Open Partial Closed Open Open 2.5 to 4+ Closed Closed Partial Open Partial Closed Sustained Aero Choke 4+ to 7 Closed Closed Closed Closed
Vehicle TriJet Engine Set Front View Rear View TE Nozzles Open ERJ Nozzle Core Burning Flaps DMRJ Top View Ejector Ramjet Engine Inlet Ejector Ramjet Engine VG Section Nozzle Released For the Public
Aerojet Combined Cycle Inward-turning Inlet (ACCII) US Patent 7,216,474 Off-the-Shelf Front View Turbine Engine ACCII Wind Tunnel Test Model TriJet w/ ACCII Ejector Ramjet Core Burning Dual Mode Ramjet Over 8,000 Data Points Collected from Mach 0 to 4.6 Turbine Engine Demands Met Across the Entire Mach Range, While Maintaining a Started Inlet System at Supersonic Speeds Integrated Inlet Operation with all Three Inlet Systems Back Pressured and Interacting Simultaneously Demonstrated Internal Mass Flow Redistribution Via Door Actuation and Back Pressure Demonstrated Released For the Public
Sustained Aero-Choke (SAC) Concept US Patent 7,886,516 Nozzle Flap Integrated Nozzle ERJ Flow ERJ Plume Combined Thrust Internal DMRJ Nozzle Used As DMRJ DMRJ Flow Added Combustor Area Objective • Use DMRJ/Nozzle to Provide Substantial Thrust Augmentation Over Mach 2.5 – 4.0 Range Approach • ERJ Plume Provides Sustained Aerodynamic Choke For DMRJ Combustor – Increases Effective DMRJ Combustor Area Ratio Allowing Additional Heat Release in DMRJ Part of Nozzle – Enables Robust, Mach 2.5 Ramjet Operation of DMRJ Released For the Public
“Core Burning” Reduces Wall Heat Load 40% Relative To “Wall Burning” US Patent 7,797,943 Air Fueling/Flame-holding Structure Fuel (With Isolator Function) Combusted Inlet Gas Q_wall vs ER_eff Wall Burning Mach 5 T7/Q1000 1000 Core Burning 900 T2/Q1000 Heat Load – BTU/sec 800 Q_wall (Btu) 700 600 500 400 300 200 100 0 0.4 0.5 0.6 0.7 0.8 ER_eff 8 Released For the Public
Successful Flameholding and “Core Burning” Demonstrated “Core Burning” – Flame Propagates From Center, Staying Off Wall Combustor Exit Central Flameholder Released For the Public
TriJet Addresses Current TBCC Issues Transonic Thrust Margin ……………………………………………….. Assist Turbine Engine (TE) w/ Ejector Ramjet (ERJ) Off-the-Shelf (OTS) TE/ State-of-the-Art (SoA) DMRJ Thrust Gap .. Use ERJ & Sustained Aero Choke To Bridge Gap DMRJ Cruise Thermal Management ………………………………….. Use Core-Burning To Lower Heat Load No Full Scale Ground Test Facilities …………………………………. Build Mach 6+ Vehicle and Operate w/ Robust OTS TE and SoA ERJ up to Mach 3. Normalized Install DMRJ and Use Vehicle for Vehicle Drag &Thrust “Envelope Expansion” to Mach 6 1.80 Drag 1.60 TE-Thrust 1.40 ERJ-Thrust In-Flight Envelope 1.20 SAC/DMRJ-Thrust Expansion 1.00 DMRJ (Only)-Thrust 0.80 TriJet-Thrust 0.60 0.40 0.20 0.00 0.00 1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 Flight Mach Number Released For the Public
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