FY 1989 NEW INITIATIVE

NASA HIGH SPEED CIVIL TRANSPORT TECHNOLOGY PROGRAM

(HISPECT)

e PROPULSION

e PROPULSION/AIRFRAME INTEGRATION , ; .

e FUELS & FUEL SYSTEMS '

e THERMAL MANAGEMENT

Version: Fel2_ruary 3, 1987

PLANNING PERSPECTIVE

e NATIONAL RECOGNITION THAT REVOLUTIONARY ADVANCES IN AIRCRAFT CAP ABILITIES ARE NOW TECHNICALLY FEASIBLE

- WHITE HOUSE OSTP .. EAGLE REPORT .. '

- NASA/NRC .. YE,AR .lOOO REPORT ..

- MILITARY FORECAST II·.REPORT

e CIVIL MARKET. TRENDS AND FORECASTS IDENTIFY NEED FOR HIGH~SPEED, LONG-RANGE TRANSPORTS

• PROPULSION TECHNOLOGIES ARE THE KEY CRITICAL TECHNOLOGIES · ;

ADVANCED PROPULSION HAS LED TO NEW GENERATIONS OF AIRCRAFT

GENERAL AVIATION

ROTORCRAFT

FIGHTERS

TRANSPORTS .

MAJOR TECHNICAL ISSUES

e WHAT CRUISE SPEED? TECHNICAL OPPORTUNITIES &. MARKET WINDOWS

. • WHAT FUEL? DESIGNER JET FUELS, EHC, CH4 , LH2 .

• HOW TO ACHIEVE ACCEPTABLE COMMUNITY NOISE LEVEL? .i

o I

- EXISTING AIRPORTS &. HUGE TECHNICAL CHALLENGE ! J

-DEDICATED AIRPORTS &. HUGE ECONOMIC CHALLENGE

• SONIC BOOM

- WHAT IS ACCEPTABLE?

- HOW TO ACIDEVE OVERLAND FLIGHT?

' '

• ACHIEVING . SUFFICIENT AIRCRAFT/ENGINE PERFORMANCE TO PERMIT ECONOMIC VIABILITY .

TARGET MISSION FOR HIGH- SPEED CIVIL TRANSPORT

TARGET MISSION

RANGE -

SPEED -

ALTITUDE -

PAYLOAD­

SONIC BOOM

AIRPORT NOISE -

FUEL -

6500 N.M

MACH 3-6

>90,000 FT.

300 PAX

< I psf

FAR 36- III

NON­CRYOGENIC

.

OVERALL PHILOSOPHY FOR HISPECT

• PREMATURE TO SELECT A SINGLE ~F.Sr PROPULSION CONCEPT NOW

• FOCUSED EFFORTS REQillRED TO DETERMINE CHARACTERISTICS OF SEVERAL CANDIDATE .CONCEPTS

' ..... -SUPERSONIC THR.U-FLOW FAN/COMPRESSOR -ATR

'

-SUPERSONIC THRU-FLOW ENGINE -RATS

• A BASE R&T PROGRAM ALSO NEEDED TO ENABLE MANY CONCEPTS

• STRUCTURE PROGRAM WITH NEAR TERM (e.g.. ATR) AND FAR TERM (e.g.. SUPERSONIC 11IR.OUGHFLOW FAN/ENGINE) OBJECTIVES '

..

GOAL

ESTABLISH THE PROPULSION TECHNOLOGY THAT WILL ENABLE LONG- RANGE . MACH 4-5 CIVIL .tRANSPORTS To BECOME A REALITY :

·.

TRIP TIME 6500 NM

100.000

. ALTITUDE

so.ooo

WHY MACH 4- 5?

13-1/2 hr. 6 hr.

2-1/2 psf SONIC BOOM

2-l/2 hr. 1-3/4 hr.

·DIMINISIDNG GAIN---+ < 1 psf

1----- TURBOMACIDNER Y & NO N-cR YO~--.. -------------?-----------+ FUELS POTENTIAL

Ozone

/

0 1 2

~::;;....--'""" \

~ \ ~ _... _._ "" - TECHNICAL \

/ \ CHALLENGE I ) - MARKET . I

CURRENT I O~PORT. / TECHN. / //

/ / // ./

/

3 4 5 6 FliGHT , MACH NO.

7 8

MACH 4-5 UNIQUE PROPULSION TECHNOLOGY CHALLENGES

CURRENT DUAL-CYCLE CONCEPTS:

-VCE NEED - TURBORAMJET -ATR

ENGINE CRUISE Isp @ 1600 ~2100

MACH 4 -'

.. .

ENGINE T#W 4-5 AJ 10 . ; .. / '

FUEL 014 NON-CRYOGENIC f ~

NOISE FAR STAGE II FAR STAGE III

CONCLUSION: NOVEUUNCONVENTIONAL TURBOMACHINERY CONCEPTS SHOULD BE PURSUED AS WELL .AS TRADITIONAL TURBO RAMJET

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SUPERSONIC . DIFFUSER

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SINGLE STAGE SUPERSONIC FAN

-DUCT NOZZLE

SUBSONIC . PERSON

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DIFFUSER· . . · ., .DIFFUSER---

CONVENTIONAL TURBOFAN .::' ;; SUPERSONIC FAN ENGINE ·-:· \ .· . ·:.. ...

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SUPERSONIC FAN ENGINE FEATURES . IMPLICATIONS • SHORT, ALL SUPERSONIC INLET . • LOWER WEIGHT, LOWER INLET DRAG • SINGLE STAGE SUPERSONIC FAN • LOWER WEIGHT AND COST, RUGGED :B.LADING

. - . . ' :

• BPR DECREASES WITH Mo ·. • HIGHER CRUISE THRUST

. .. .. . .-· . .. .._.,

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POTENTIAL PROPULSION CONCEPTS

•.

TECHNOLOGY PROPULSION INTERNAL PERFORM. TARGET CHALLENGE CONCEPT CORE FLOW GOAL FUELS

ATR 1URBORAMJET

STOICIL TURBOFAN

SS FAN-ATR SS FAN-TURBOFAN , REMOTE AUG. TURBOFAN

SUBSONIC

STOICIL TURBOFAN/JET SUPERSONIC

BASE JPX. EHC

+6 FBC

+26 EHC.CH4

CONCEPTS REVIEWED/UPDATED THROUGHOUT PROGRAM TO ASSURE CRITICAL TECHNOLOGIES BEING ADDRESSED . ' ..

I

--·HIGH SPEED TRANSPORT STUDIES ·

-- . PROPULSION CONCEPT EVALUATION TEAMS

., .. . .,

HISPECT PROPULSION TECHNOLOGIES CIVIL MACH 4-5

COMPONENTS • STOICIDOMETRIC TURBOMACillNER Y • SUPERSONIC TIIROUGHFLOW FANS/COMPRESSORS • COOLED COMPRESSORS • REGENERATORS/HEAT EXCHANGERS • MACH 5 INLETS & SS DUCTING • LOW NOISE EXHAUST SYSTEMS • SUPERSONIC HYDROCARBON COMBUSTORS

I

SYSTEMS • REGEN. ATR (WITH & W/0 SS FAN) • SUPERSONIC THROUGHFLOW TURBOFAN/JET • STOICHIOMETRIC TURBORAMJETS • REMOTE AUGMENTED THRUST SYSTEM (RATS) • THERMAL MANAGEMENT • PROPUI.SION/A.IRFR.AME INTEGRATION (PROPULSION

EFFECTS) • FUELS & FUELS DISTRIBUTION