for Reusable Hypersonic Vehicles Dr. Adam Siebenhaar Director - - PowerPoint PPT Presentation

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for Reusable Hypersonic Vehicles Dr. Adam Siebenhaar Director - - PowerPoint PPT Presentation

Apr 29, 2023 27 likes •130 views

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

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SLIDE 1

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

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SLIDE 2

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

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SLIDE 3

0.0 0.2 0.4 0.6 0.8 1.0 1.2 0.0 1.0 2.0 3.0 4.0 5.0 6.0 7.0

Vehicle Drag TE-Thrust DMRJ-Thrust

Normalized Vehicle Drag (Drag/Dragmax) & Thrust (Thrust/Dragmax)

Insufficient Net Transonic Thrust DMRJ Thermal Management Lack of Full Scale Ground Test Facilities

Flight Mach Number

Current Major Combined Cycle Propulsion Issues

Released For the Public

TE – DMRJ Thrust Gap

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SLIDE 4

Aerojet TriJet Concept Operation

Inlet Capture Area Mach 2.5 TE (Available Now) Mach ~4+ Ejector Ramjet Mach 3.5 -7 Dual Mode Ramjet Front Views

Variable Geometry Doors

Port Engine

Vertical Cut DMRJ DMRJ

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

Vertical Cut

ACCII Wind Tunnel Test Model

Released For the Public

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SLIDE 5

Vehicle TriJet Engine Set

TE Nozzles Open ERJ Nozzle Flaps

Front View Rear View

Core Burning DMRJ

Inlet VG Section Ejector Ramjet Engine Ejector Ramjet Engine Top View Nozzle

Released For the Public

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SLIDE 6

Aerojet Combined Cycle Inward-turning Inlet (ACCII)

Off-the-Shelf Turbine Engine Front View TriJet w/ ACCII ACCII Wind Tunnel Test Model 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

US Patent 7,216,474

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SLIDE 7

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

Sustained Aero-Choke (SAC) Concept US Patent 7,886,516

Integrated Nozzle Nozzle Flap

Combined Thrust

DMRJ

ERJ Plume Internal DMRJ Nozzle Used As Added Combustor Area DMRJ Flow

ERJ Flow Released For the Public

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SLIDE 8

8

“Core Burning” Reduces Wall Heat Load 40% Relative To “Wall Burning” US Patent 7,797,943

Fuel Fueling/Flame-holding Structure (With Isolator Function) Air Inlet Combusted Gas

Q_wall vs ER_eff

100 200 300 400 500 600 700 800 900 1000 0.4 0.5 0.6 0.7 0.8 ER_eff Q_wall (Btu) T7/Q1000 T2/Q1000

Wall Burning Core Burning

Heat Load –BTU/sec

Mach 5

Released For the Public

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SLIDE 9

Successful Flameholding and “Core Burning” Demonstrated

“Core Burning” – Flame Propagates From Center, Staying Off Wall Central Flameholder Combustor Exit

Released For the Public

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SLIDE 10

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. Install DMRJ and Use Vehicle for “Envelope Expansion” to Mach 6 Normalized Vehicle Drag &Thrust

Flight Mach Number 0.00 0.20 0.40 0.60 0.80 1.00 1.20 1.40 1.60 1.80 0.00 1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 Drag TE-Thrust ERJ-Thrust SAC/DMRJ-Thrust DMRJ (Only)-Thrust TriJet-Thrust In-Flight Envelope Expansion Released For the Public