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T S AGI RESEARCH CAPABILITIES TO ADDRESS AVIATION ENVIRONMENTAL - - PowerPoint PPT Presentation

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CENTRAL AEROHYDRODYNAMIC INSTITUTE CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. NAMED AFTER PROFESSOR N.E. ZHUKOVSKY ZHUKOVSKY T S AGI RESEARCH CAPABILITIES TO ADDRESS AVIATION ENVIRONMENTAL IMPACT ISSUE Sergey

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

TSAGI RESEARCH CAPABILITIES TO ADDRESS AVIATION ENVIRONMENTAL IMPACT ISSUE

Sergey Chernyshev

Executive Director TsAGI, Russia

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Contents

14.10.2012 2

 AVIATION ENVIRONMENT ISSUES  NOISE  SONIC BOOM  EMISSION  ALTERNATIVE AVIATION FUEL

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Aviation Impact on Environment

14.10.2012 3

Aircraft Environment Issues

Noise

  • Health deterioration
  • Hearing impairment
  • Disturbances of vocal

communication Emission

  • Respiratory disorders
  • Toxic symptoms
  • Discomfort

Sonic boom

  • Orientation response of people
  • Starting
  • Sleep disruption

Greenhouse gases emissions, contrails

  • Global warming
  • Climate change

Airport environment

  • Pollution

JAXA Aeronautics Symposium in Nagoya Stratosphere Troposphere Ground layer Ozone layer destruction Climate change Impact near ground surface NOx CO2 NOx H2O Solid particles Noise Emission

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

14.10.2012 4

ICAO Requirements in Airport Proximity

1960 1970 1980 1990 2000 2010 2020 year ΔEPN dB –10 10 –20 20 –30 30 –40 40 –50 50 –60 60 –70 70 –80 80 –90 90 –100 100 Airplanes noise Chapter 2 Chapter 3 Chapter 4 NOx emissions % relative to 1985 emissions

Spatial location of control points (CP) for acoustic certification of commercial airplanes

DESCENT CLIMBING RUNWAY 120 m CT3 CT1 (Turbofan) 450 m 300 m CT2 CT1 (Turboprop) 650 m

JAXA Aeronautics Symposium in Nagoya

NOx emissions, g/kN Pressure ratio (H = 0, M = 0) 120 100 80 60 40 20 10 15 20 25 30 35 40 45 50 π∑ ICAO standards ICAO targets

ICAO proposals to toughen NOх emissions during take-off and landing Controlled combustion products: – Carbon oxide (СO) – Unburned hydrocarbons (CH) – Nitrogen oxides (NOx) – Soot (С)

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Environment Target Goals for the Russian Aviation

14.10.2012 5

Target goals Baseline (2010) Dynamics of target goals 2015 2020 2025 2030 Accidents reduction 1 2.5 5.0 7.0 8.5 Noise reduction relatively to ICAO Chapter 4 (by EPN dB) 7 12 20 25 30 NOx emission reduction relatively to ICAO 2008 standards (by %) 100 (2008) 20 45 65 80 Fuel consumption and СО2 emission reduction (by %) 100 10 25 45 60

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Contents

14.10.2012 6 JAXA Aeronautics Symposium in Nagoya

 AVIATION ENVIRONMENTAL ISSUES  NOISE  SONIC BOOM  EMISSION  ALTERNATIVE AVIATION FUEL

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Aircraft Noise Sources

14.10.2012 7 JAXA Aeronautics Symposium in Nagoya

  • 1. Jet noise

The principal components determining the noise of a modern passenger aircraft are: fan and turbine noise, jet noise and airframe noise. All the above sources of aerodynamic noise turn out to be important at different flight stages. Only a balanced reduction of all the above sources can lead to the overall desired aircraft noise reduction.

  • 2. Inlet and aft fan noise, turbine noise
  • 3. Airframe noise
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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Acoustic Anechoic Chambers

14.10.2012 8

Maximum sound pressure level 160 dB Test section volume 211 м3 Test section dimensions 9,6×5,5×4,0 м3 Operational frequency range 160 – 20000 Hz Stagnation temperature 293 K

AK-2

Anechoic chamber (AC), m3 14.0×11.5×8.0 Free volume, m3 12.2×9.7×6.3 Reverberation chamber 1 (RC1), m3 6.4×6.4×5.15 Reverberation chamber 2 (RC2), m3 6.6×6.4×5.15 Operational frequency range, Hz 80 … 16000

AK-11

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Aircraft Engine Noise Reduction

14.10.2012 9 JAXA Aeronautics Symposium in Nagoya

Improved acoustic liners in the air inlet Fan noise control Combustion chamber noise control Jet noise control Air inlet channel shape control Turbine noise control Lining of mixing chamber walls Outer circuit channel walls fully treated with liners

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Fan Noise Reduction Methods

14.10.2012 10

Key Issues:

  • Fan aerodynamics performance
  • Fan blade stability and stall margin erosion
  • Manufacturing cost and complexity
  • Validation of CFD prediction methods

Expected noise reduction:

  • Fan tone intake noise

2 to 4 dB at take-off

  • Fan tone exhaust noise up to 2 dB

Approach:

  • To remove or weaken shocks at the fan blades
  • Simultaneous optimization of aerodynamic and

acoustic performance

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Engine Noise Reduction by Advanced Acoustic Liners

14.10.2012 11 JAXA Aeronautics Symposium in Nagoya

500 800 1250 2000 3150 5000 Frequency, Hz 18 15 12 9 6 3 Efficiency, dB Composite double- layer liners Conventional liners

First generation liners (single-layer)

Metallic Composite Perforated skin Honeycomb filler Skin Box-type filler Perforated skin

Second generation liners (double-layer)

Metallic Composite Perforated skin Metallic mesh Skin Perforated filler

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Fan Noise Reduction by Acoustic Liners

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Method Estimated noise reduction TRL Main problems Seamless air inlet liners Suction noise: 1…4 dB during approach (in service with А380) 7…9 Improving liners manufacturing and repair technology Tapered air inlets Suction noise: ~ 3 dB 4…6 Aerodynamics, trade-off between cruise and climb Lining of air inlet lip Suction noise: 1…3 dB 4…6 Integration with anti-icing systems Lining of hub surface Acoustic power at outlet: 1…3 dB 3…4 Lacking full-scale verification data

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Low Noise Nozzle Configurations

Variety of nozzle configurations are suggested for the experimental jet noise reduction

14.10.2012 13 Noise reduction of jet emanating from chevron nozzle 25 50 100 200 400 800 f, Hz Round nozzle Chevron nozzle 5 dB Noise JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Jet Noise Reduction Methods

14.10.2012 14

Method Expected noise reduction TRL Open issues Fixed geometry chevrons 1…4 EPN dB during roll and climb 6…9 Nacelle-Pylon integration for best aerodynamic performance Variable geometry chevrons 0.5…1.0 EPN dB during roll and climb 6 Reliability, maintainability and manufacturability Geared turbofan, m > 10 bypass ratio Depending on

  • peration regime

6…7 Higher structural weight and drag; maintainability Long channel with forced flow mixing ~ 1…2 EPN dB during roll and climb 6…9 long fairing nacelles for m ≈ 4…6, typically applied on regional and business aircraft

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

V = 100…180 m/s f = 6…12 kHz D ~ 5 cm

Noise Control by Plasma Actuators

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500 1k 1.5k 2k 2.5k 3k 3.5k 4k 4.5k [Hz] 45 50 55 60 65 [dB/20u Pa] w/o plasma actuators with plasma actuators

Noise level improvement – 1.3 dB The concept is based on direct control of noise radiation by Dielectric Barier Discharge (DBD). Vlasov–Ginevsky effect.

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

14.10.2012 16

Airframe Noise Reduction: Slats

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Airframe Noise Noise Reduction: Landing Gear

14.10.2012 17 JAXA Aeronautics Symposium in Nagoya

50 65 50 100 150

x, cm P, dB 5 dB

microfone 1

Noise control concept is based on shaped chassis rack and self-tuning system for major mode noise suppression. Patent of TsAGI No. 2293890

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Landing Gear Noise Reduction Methods

14.10.2012 18 JAXA Aeronautics Symposium in Nagoya

Method Overall noise reduction efficiency TRL Expected TRL = 6 time target Expected TRL = 8 time target Main problems Fairings and covers Up to 3 dB 6 Weight, heat emission, maintainability Low-noise chassis rack Up to 5 dB 3…4 2013 2015 Structural and systems integration

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Future Aircraft: Low Noise and Low Fuel Consumption

14.10.2012 19

Level 2012

10%

Noise Fuel consumption Distributed Fans Low noise embedded propulsion Future Low Noise Aircraft:

Blended wing concept

Podded engines with variable nozzles

Mixed exhaust with extensive acoustic liners

Power managed take-off Blended wing concept

JAXA Aeronautics Symposium in Nagoya −30 EPNdB

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Contents

14.10.2012 20 JAXA Aeronautics Symposium in Nagoya

 AVIATION ENVIRONMENTAL ISSUES  NOISE  SONIC BOOM  EMISSION  ALTERNATIVE AVIATION FUEL

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Low Boom Super Sonic Business Jet

14.10.2012 21 JAXA Aeronautics Symposium in Nagoya HISAC: TsAGI–SUKHOY

−0.05 0.05 0.10 0.15 0.20 − 60 − 40 −20 20 40 60

t, s

G = 51 t G = 58.5 t G = 56.5 t

H, m L, dbA P, Pa

Near field Far field Bow shock Pressure signature p(t) p t t p

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Contents

14.10.2012 22 JAXA Aeronautics Symposium in Nagoya

 AVIATION ENVIRONMENTAL ISSUES  NOISE  SONIC BOOM  EMISSION  ALTERNATIVE AVIATION FUEL

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Emission Factor OF Various Transportations

  • ref. DLR, 2008

14.10.2012 23 JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Air Transport Emission Modeling

14.10.2012 24 Air Traffic СО2 emission, including forecast

Routes over Russia

Contrails

years CO2 emission, Mt modeling ↔ forecast JAXA Aeronautics Symposium in Nagoya 1° 1° 1 km Air space cell

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Low Drag Due to Flow Control

14.10.2012 25 JAXA Aeronautics Symposium in Nagoya

Speed and range increase 8–10% Fuel burn reduction –(5–7)% Take-off and landing speeds reduction –(10–15)% Runway length reduction –(30–35)% Using jet blowing system provides:

ΔK = 1.2 Flow separation Slot nozzle M = 0.78 K 12 10 8 0.2 0.4 0.6 0.8 1.0 CL Blowing Jet Shock M1 = 1 M1 > 1 Slot Compressed air supply δз 1 2 3 0.7b A–A A A 1 3 4 5 2 1 Cruise δз = 0° 2 Take-off δз = 30° 3 Landing δз = 60° 1 Bleeding air from fan 2 Bleeding compressed air from compressor 3 Control and cut-off valves 4 Slot nozzle 5 Ring channel

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Active Aeroelasticity Concept

14.10.2012 26

Main benefits of active structures :

  • 4–6% increase in lift-to-drag ratio
  • Control efficiency increase by 30–40%
  • Fuel efficiency increase by 5–7%
  • Structure weight reduction by 6–8%
  • Noise reduction by 7–10 dB
  • Innovative controls having high efficiency

at all flight regimes: take-off, landing, cruise

  • Main tasks – engineering, materials,
  • ptimization, life

Smart controls based on SDS- structures provide 30–40% gain in control efficiency Selectively Deformable Structure (SDS)

JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Number of Engines: Environment Impact

14.10.2012 27 JAXA Aeronautics Symposium in Nagoya Conventional configuration, two engines Conventional configuration, three engines Take-off thrust-to-weight Noise Fuel burn per 1 pass.·km Direct operating costs 100 89 80 85 90 95 100 105 Long-haul aircraft-2 Long-haul aircraft -3 % 100 96 80 85 90 95 100 105 Long-haul aircraft -2 Long-haul aircraft -3 100 97 80 85 90 95 100 105 Long-haul aircraft -2 Long-haul aircraft -3 % 100 100,7 80 85 90 95 100 105 Long-haul aircraft -2 Long-haul aircraft -3 % −12.6 ЕpNдБ

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

AERIAL REFUELING

14.10.2012 28 JAXA Aeronautics Symposium in Nagoya

  • Noise reduction in the airport area due to reduced

aircraft weight up to 35–40% for long-haul airplanes

  • Reduction of air transportation volumes due to

increasing number of «point to point» routes

  • 15–20% less fuel burn

Il-96-300 q, гр/пасс.·км 30 % MC-21-200 20 % 25 % Including fuel burnt by air refueller 25 20 15 2000 4000 6000 8000 10000 L, km

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Contents

14.10.2012 29 JAXA Aeronautics Symposium in Nagoya

 AVIATION ENVIRONMENTAL ISSUE  NOISE  SONIC BOOM  EMISSION  ALTERNATIVE AVIATION FUEL

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Condensed Aviation Gas Fuel

30

1. Condensed aviation gas fuel is «greener» compared to conventional kerosene: – СО2 5–10% less emission – low NOx and CO – very low solid particles (soot) 2. Huge amounts of propane-butane gas are burned at the oil development sites contributing to greenhouse gas emission in the atmosphere. Russia territory gas torches thermal wakes

14.10.2012 JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Condensed Gas Fuel Aircraft

14.10.2012 31 JAXA Aeronautics Symposium in Nagoya

Mi-8ТТ helicopter

Condensed gas fuel for near and middle term fuel strategy in Russia

Ilyushin-114 regional turboprop Gas fuel tanks

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Cryogenic Fuel Aircraft

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Tupolev-155 Aircraft

Cryogenic gas fuel Tupolev-155 test

  • bed. Flight demonstration of

cryogenic methane and hydrogen for one of its three engines

14.10.2012 JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

Cryoplane

33 Higher bypass ratio turbofan Heat insulated cryogenic tanks Tail open rotor High aspect ratio swept wing with cooled upper surface

Critical technologies:

  • High-power fuel cells (2–3 МW)
  • Superconductivity electric engines, the 50–60 К

working temperature may be provided by the cryogenic hydrogen fuel

% 75 37 32 75 97 84 10 20 30 40 50 60 70 80 90 100 110

Modern technological level

Energy consumption Fuel burn

Long-haul aircraft-2030 (kerosene) Long-haul aircraft-2030 (hydrogen) Long-haul aircraft-2030 (integrated power plant, hydrogen)

0.56 0.52 0.47 Specific fuel consumption, kg/kG·h The highest modern level Increase

  • f engine

bypass ratio Integrated power plant −7% −16% 14.10.2012 JAXA Aeronautics Symposium in Nagoya

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CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROFESSOR N.E. ZHUKOVSKY

14.10.2012 34 JAXA Aeronautics Symposium in Nagoya

Thank You for Your Attention!