Hypersonic: Combined Cycle Engine Mode Transition

National Aeronautics and Space Administration

www.nasa.gov

A Turbine Based Combined Cycle Engine

Inlet Model and Mode Transition

Simulation Based on HiTECC Tool

An inlet system is being tested to evaluate methodologies for a turbine based

combined cycle propulsion system to perform a controlled inlet mode

transition. Prior to wind tunnel based hardware testing of controlled mode

transitions, simulation models are used to test, debug, and validate potential

control algorithms. One candidate simulation package for this purpose is the

High Mach Transient Engine Cycle Code (HiTECC). The HiTECC simulation

package models the inlet system, propulsion systems, thermal energy,

geometry, nozzle, and fuel systems. This paper discusses the modification

and redesign of the simulation package and control system to represent the

NASA large-scale inlet model for Combined Cycle Engine mode transition

studies, mounted in NASA Glenn’s 10-foot by 10-foot Supersonic Wind

Tunnel. This model will be used for designing and testing candidate control

algorithms before implementation.

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A Turbine Based Combined Cycle Engine Inlet

Model and Mode Transition Simulation Based

on HiTECC Tool

Jeffrey Csank and Thomas Stueber

NASA Glenn Research Center

Cleveland, Ohio

2012 Joint Propulsion Conference

Atlanta, GA

July 29 – August 1, 2012


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Outline

• Introduction

– NASA Hypersonics Project

– Combined Cycle Engine Large-scale Inlet for Mode transition

eXperiments (CCE-LIMX)

• High Mach Transient Engine Cycle Code (HiTECC)

Simulation

– Updating HiTECC to match CCE-LIMX specifications

– New model to support CCE-LIMX Experiments

• Conclusions and Future Work

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NASA Hypersonics Project

• Hypersonics Research

– Develop tools and technologies to design and control

Reusable Airbreathing Launch Vehicles (RALVs) to provide

hypersonic flight through the Earth’s atmosphere and create

routine, airline-type access to space

– Two-stage-to-orbit (TSTO) vehicles

• One vehicle responsible for horizontal takeoff and acceleration

to staging point.

• Horizontal takeoff and landing enhances launch, flight and

ground operability

– Launch pad not needed

– Flexible operations and quick turnaround time (Aircraft like

operations)

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NASA Hypersonics Project

• Turbine Based Combined Cycle (TBCC) propulsion

system

– Turbine Engine and Dual-Mode Scramjet

• Combined Cycle Engine Large-scale Inlet for Mode

transition eXperiments (CCE-LIMX)

• Hardware designed and built in the NASA Glenn

Research Center 10ft x 10ft Supersonic Wind Tunnel

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CCE-LIMX Model

Low-Speed Flow Path

(turbine engine)

High-Speed Flow Path

(DMSJ engine)

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CCE-LIMX Model

Pre-compression forebody plate

Isolator High-Speed Plug

Variable Ramp

High Speed Cowl

Low-Speed Cowl / Splitter

Tunnel Floor

Tunnel Ceiling

Pivot for AoA

F l o w

Low-Speed Plug

30 feet

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Over Mounted Low-Speed Flow Path Under Mounted High-Speed Flow Path


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CCE-LIMX Model



Variable Ramp

High Speed Cowl


Tunnel Floor

Tunnel Ceiling

Pivot for AoA

Overboard

Bypass

F l o w

Low-Speed Plug

30 feet

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Inlet Unstart Region Inlet Start Region

Throat

Normal Shock

Increased Stability Margin

Increased Performance

Diffuser

CCE-LIMX LSFP Terminology

High mass recovery

High pressure recovery

Low distortion

Low drag

Started Inlet Un

Compressor stall

Combustor flame-out

Causes of Inlet Unstart: Compressor stall

Free stream changes

Airflow Direction

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CCE-LIMX Test Plan

• Phase 1 – Inlet characterization and performance testing

– Static inlet operating points

– Mode transition schedule

• Phase 2 – System identification

– Step response

– Sinusoidal sweep response

• Phase 3 – Controls testing

– Disturbance rejection testing

– Controlled mode transition

• Phase 4 – Propulsion system testing

– Turbine engine for LSFP

– Dual-mode combustor for HSFP

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Guidance Navigation and Control Team

• Develop tools and procedures to streamline:

– Experimental data analysis

– Inlet mode transition controls design

– Controls evaluation

• Simulation models:

– LArge Perturbation INlet (LAPIN)

– Aerosim interactive simulation

– High Mach Transient Engine Cycle Code (HiTECC)

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HiTECC Simulation

• High Mach Transient Engine Cycle Code (HiTECC)

• Simulation package originally developed by

SPIRITECH Advanced Products Inc.

• Demonstrate all modes of operation of a TBCC

propulsion system

– Afterburner, turbine engine, and dual-mode scramjet

– Simulate mode transition sequence of events

• Designed to be generic and modular

– Inlet geometry described using the Mathworks® SimscapeTM

– Fast prototyping of inlet designs

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Thermal Management /Fuel System Models

Control System Hydraulics Model

Turbo Jet Engine Model

Dual Mode Scramjet Model

High Mach Transient Engine Cycle Code (HiTECC)

Propulsion Models

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Thermal Management / Fuel Systems

• Simulates fuel flow, fluid energy, and thermal energy

transfer for both the LSFP and HSFP

• One-dimensional compressible flow solver allows a

variety of fuels, including hydrogen, to be modeled

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2

Pfuel

1

T_ABLiner

V+

-

PS

+-

Tt

VolumeRef

Pt

A

B

Area Out

dens

cp

v isc

v sonic

Tank With Return1

ht

m

A B

ht

m

A B

f(x)=0

PSS

PSS

PsBS

A

AreaA

densA

cpA

v iscA

v sonicA

B

AreaB

densB

cpB

v iscB

v sonicB

Positive Displacement Pump

A

AreaA

densA

cpA

v iscA

v sonicA

B

AreaB

densB

cpB

v iscB

v sonicB

Pipe7

A

AreaA

densA

cpA

v iscA

v sonicA

B

AreaB

densB

cpB

v iscB

v sonicB

Pipe2

A

AreaA

densA

cpA

v iscA

v sonicA

B

AreaB

densB

cpB

v iscB

v sonicB

Pipe

PSS

Res_TF_Pump_wSimscape

FluidReference

Simscape

FluidProperties

G

Rotational Speed

Torque

+

-

R

C

DC Motor

Current

Power Remaing

+

-

Battery

Qpanel Tpanel

A

Area A

dens A

cpA

v iscA

v sonicA

B

Area B

dens B

cpB

v isc B

v sonicB

AB Panel

2

DC Motor Resistance

1Qpanel


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Hydraulics Model

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• Simulates the kinematic features of the variable inlet

and nozzle for both flow paths

• Models the dynamic response of the hydraulic fluid

• Models for the power storage and generation for

pumping the hydraulic fluid

3

Relief Valve

2

Tank Supply

1

Tank Return

f(x)=0

Solver

Configuration1

PSS

V P R

Reservoir

PS S

PS SPS S

PS S

PSS

QA

B

Ideal Hydraulic Flow

Rate Sensor2

QA

B

QA

B

Ideal Hydraulic Flow

Rate Sensor

AB

P

Ideal Hydraulic

Pressure Sensor

S A

B

2-Way Directional

Valve

1

Shut Off Valve


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Propulsion System

• Variable Inlet (P,T,W)

• Gas Turbine (with afterburner)

• Dual Mode Scramjet

• Assume Started Low-Speed and High-Speed Inlets

(No external normal shocks)

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HiTECC Configured for CCE-LIMX Inlet

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High Mach Transient Engine Cycle Code

(HiTECC)

CCE-LIMX

Update Model to

Match CCE-LIMX

Model

Wind Tunnel Model

for Testing and

Evaluation of

Control Algorithms


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SimScape® (The Mathworks, Inc)

SimMechanics®

• Models 3-D rigid-body mechanical systems

• Analyzes motion and calculates forces

• Visualize and animate mechanical system

dynamics with 3-D body geometry

• Integration in Simulink

• Provides interfaces to CAD platforms

(Pro/E®)

SimHydraulics®

• Models hydraulics power and control

systems

• Library of components (pumps, valves,

accumulators, pipelines)

• Customizable library of common hydraulic

fluids

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B F

Weld1

B F

Weld

CS3 CS2

RootPartRootGround

B F

Revolute1

B F

Revolute

CS2

PEND-1

CS2 CS3

PEND

Env

CS3 CS2

HOOK


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CAD Drawing (Pro/E®)

Simulink Model

HiTECC Simulink Model

SimMechanics Link

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Redesign Geometry, Actuators, and Control

Systems

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100 150 200

-30

-20

-10

X Position, in

Y P

ositio

n,

inMach 4.0

100 150 200-2

0

2

X Position, in

Are

a E

rror,

%

Mach 4.0

100 150 200

-30

-20

-10

X Position, in

Y P

ositio

n,

in

Mach 3.1

100 150 200-2

0

2

X Position, in

Are

a E

rror,

%

Mach 3.1

100 150 200

-30

-20

-10

X Position, in

Y P

ositio

n,

in

Mach 2.5

100 150 200-2

0

2

X Position, in

Are

a E

rror,

%Mach 2.5

CCE-LIMX HiTECC


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HiTECC Subsonic Volume Initial Conditions

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Supersonic

Flow

Subsonic

Flow

No

rmal

Sh

ock

W16 P15

T15 P17

T17 P19

T19 W18

dxdt


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HiTECC Initial Conditions

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Propulsion

Hydraulic/Kinematic

Control

Thermal


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HiTECC Initial Conditions

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Propulsion

Hydraulic/Kinematic

Control

Thermal Control

Switch

Hydraulic/Kinematic

Sw

itch


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Mode Transition

• Mode transition

with HiTECC

– Mach 3.75

– Afterburner

shutdown

(PLA 150 -100)

– Start DMSJ

– Transition power

– Shutdown Engine

– Close off LSFP

– Continue with

mission

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0 2 4 6 8 10 120

2

4

6

8

10

12

Time, s

Altitude (10,000 ft)

Mach Number

0 2 4 6 8 10 120

50

100

150

Time, s

Pow

er

Lever

Angle

, %

Turbine

DMSJ


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Mode Transition

• During mode

transition,

propulsion system

must produce

enough thrust to

keep vehicle at

Flight Condition.

• TBCC produces

thrust between the

min/max bounds

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0 2 4 6 8 10 120

2000

4000

6000

Time, sT

hru

st,

lbf

Turbine

DMSJ

0 2 4 6 8 10 120

2000

4000

6000

Time, s

Tota

l T

hru

st,

lbf


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Mode Transition Plots

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0 2 4 6 8 10 120

0.2

0.4

0.6

0.8

Time, s

Pre

ssure

Ratio

0 2 4 6 8 10 12182

184

186

188

190

Time, s

Shock P

ositio

n,

in


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CCE-LIMX Model



Variable Ramp

High Speed Cowl


Tunnel Floor

Tunnel Ceiling

Pivot for AoA

Overboard

Bypass

F l o w

Low-Speed Plug

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• Testing candidate mode transition and shock position

control algorithms before implementation

• Compare performance of HiTECC to wind tunnel data

model validation


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Replacement of Turbine Engines with a Plug

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100% 0%

Plug

Air Flow

Plug Plug Plug Plug

Plug Position

0 10 20 30 40 50 60 70 80 90 1000

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Plug Position, % Full StrokeP

ressure

Ratio

0 10 20 30 40 50 60 70 80 90 1000

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1


ressure

Ratio

0 10 20 30 40 50 60 70 80 90 1000

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1


ressure

Ratio


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Addition of the Cold Pipe Volume

W16

P15

T15 P17

T17 P19

T19

W18

Supersonic Flow

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HiTECC Wind Tunnel Model Plots

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0 1 2 3-14

-12

-10

-8

Time, s

Split

ter,

deg

0 1 2 33.2

3.3

3.4

3.5

Time, s

LS

FP

Mass F

low

Plu

g,

in

0 1 2 3165

170

175

Time, s

Shock P

ositio

n,

in

0 1 2 30.2

0.4

0.6

0.8

Time, s

Pre

ssure

Ratio

No CP

CP


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HiTECC Wind Tunnel Model Plots

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0 0.5 1 1.5 2 2.5-14

-12

-10

-8

Time, s

Split

ter,

deg

0 0.5 1 1.5 2 2.50

2

4

6

Time, s

Bypass G

ate

, sq in

0 0.5 1 1.5 2 2.5165

170

175

180

Time, s

Shock P

ositio

n,

in

0 0.5 1 1.5 2 2.5

0.4

0.5

0.6

0.7

Time, s

Pre

ssure

Ratio

No CP

CP


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Conclusions

• CCE-LIMX Experiments

– Accomplished Phase I and II of testing

• Developed a mode transition schedule

• Collected experimental data to be used for model development

• GN&C Team

– Updated HiTECC model to match the CCE-LIMX inlet

geometry

– Fixed and improved the HiTECC code

– Created a new model based off HiTECC to be used for:

• Model validation against experimental data

• To be used for control design and evaluation

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Future/Ongoing work

• Compare HiTECC to captured wind tunnel data.

Results will be published and presented at the 2012

JANNAF Conference in Monterey, CA, 12/2012.

• Use HiTECC to design shock position control

algorithms. Results will be published and presented

at the 2012 JANNAF Conference in Monterey, CA,

12/2012.

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Thank you

Any Questions?

Hypersonic: Combined Cycle Engine Mode Transition

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