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© COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES A Practical Approach For Inerting Systems on Commercial Aircraft and.

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Presentation on theme: "© COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES A Practical Approach For Inerting Systems on Commercial Aircraft and."— Presentation transcript:

1 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES A Practical Approach For Inerting Systems on Commercial Aircraft and the Development of Industry Standards Presented by Phil Jones & Brian Greenawalt Shaw Aero Devices

2 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 2 History of Recent Commercial Inerting FAA proposed concepts for practical inerting of commercial aircraft fuel tanks Storage of nitrogen enriched air in the ullage of the tank Use of different flow modes in phases of flight FAA proposed building of inerting system for 747SP Team members from FTIHWG Onboard ground inerting (OBGI) system Designed for inerting fuel tank as well as cargo fire suppression

3 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 3 OBGI System Schematic

4 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 4 System Operation Engine bleed air Pressurized air supply Cooling air Reduce bleed air temperatures Filter Remove contaminants found in bleed air Heater Reheats air after run from heat exchanger to prevent condensation Hollow fiber membrane Pressure device which reduces the oxygen level in air stream Dual orifice valve Changes the back pressure on the hollow fiber membrane Different flow modes – high flow/low purity, low flow/high purity Distribution system Injects nitrogen into tank

5 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 5 747SP OBGI System (CATIA Model)

6 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 6 Use of OBGI System Converted to OBIGGS Used as a flying test bed Proved concepts Storage of nitrogen in fuel tank ullage Dual flow mode Updating required for integration into commercial aircraft Pallet style design – space and weight restrictive

7 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES Installation

8 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 8 Installation Location FAA 747SP large installation area available Installation location was central on the aircraft Benign environment & easily accessible Relatively few personnel involved and highly aware of program

9 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 9 747SP OBGI System View from forward looking aft and up Items visible include OEA permeate bleed manifold, ASM inlets and supporting structure View from forward looking aft and up Items visible include inlet door control cable, ASM outlets, supporting structure and NEA termination point

10 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 10 Installation Location Space availability is rare on smaller aircraft Large open bays not available Proximity to the following systems: Pressurized air – bleed air Cooling air Fuel tank Environmental conditions in location No all available locations are contained within bays and may be exposed to elements or near high temperature components May be difficult for maintenance actions Human safety NEA leakage into pressurized areas or adjacent bays

11 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 11 Installation Location System size must be minimized for use in most applications Installation in close proximity to interface locations a benefit Less weight required for connections Location should be chosen for installation environment and ease of maintenance should also be considered Health and safety of passengers/crew and maintenance personnel must be considered Potential leak and accumulation of nitrogen gas

12 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES System Performance & Analysis

13 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 13 Analysis Requirements Flammability exposure model Fuel tank thermal model Inerting system performance model Aircraft information required Configuration Systems performance Flight details

14 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 14 System Performance Aircraft configuration Ullage Volume Vent configuration Space availability Weight Aircraft OBIGGS interface systems Bleed air pressure, temperature and flow profile Cooling air pressure, temperature and flow profile Maximum NEA flow Contaminants Flight details Climb & descent rate Cruise altitude & duration Other issues Allowable flammability exposure Reliability requirement Oxygen concentration

15 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 15 Inerting Performance Model Inerting performance model throughout flight profile Receives external aircraft inputs Bleed air conditions Cooling air conditions Uses performance of OBIGGS Heat exchanger Filter Hollow fiber membrane Dual orifice In-tank distribution Calculates conditions within tank Ullage space Temperature Pressure Result of the model is O 2 % in the tank Oxygen concentration in ullage space throughout flight profile

16 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 16 Single Aisle Aircraft Performance Curve

17 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 17 Flammability Exposure Model Reliability Aircraft System Performance (Bleed & cooling air, etc.) OBIGGS Performance (Ullage inert?) Tank Conditions (Ullage & pressure) Flight Details (Altitude, temperature and flight profile) Fuel tank thermal model Flammability Exposure Model Hollow Fiber Performance (NEA flow & purity) Flammable Conditions? Inert? Options: Non-flammable & not inert Non-flammable & inert Flammable & inert Flammable ¬ inert Contributes to fleet wide flammability No Yes

18 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 18 Flammability Exposure Model Determines fleet average flammability exposure Total flammable time divided by the total operating time including ground operations Flight profile randomly selected Monitor inputs throughout flight profile Temperature & pressure conditions in tank – flammable? Tank ullage oxygen concentration – inert? OBIGGS performance Producing required purity and flow of NEA Reliability – operating? Flammable time during flight profile adds to fleet wide exposure Time flammable conditions exist and tank is not inert Process is restarted until number of flights representative of fleet usage is reached

19 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 19 System Performance & Analysis Flammability exposure analysis Fuel tank conditions Temperature Pressure Fuel vapor content Oxygen concentration Inerting system performance Purity & flow rate of NEA Reliability of inerting system Total flammable time (when flammable and not inert) divided by the total operating time including ground operations

20 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES Modular Inerting System

21 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 21 Modular Inerting System Current system Pallet system requires large installation area Extra weight Pallet-airframe mounting & component-pallet mounting Pallet structure & component housing Ducting runs between components Interstitial heater Approach not acceptable for narrow body aircraft Space availability Weight penalty New configuration required for each aircraft

22 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 22 Modular Inerting System Modular inerting system Package all major components in one housing Hollow fiber membrane Filter Heat exchanger Individual housings & mountings not required Modular housing replaces need for tubing runs between components Close communication between heat exchanger and hollow fiber membrane removes need for interstitial heater Same Shaw Aero patented “Module” interchangeable across aircraft Single aisle requires 1 module, twin aisle requires 3 modules Single & twin aisle module interchangeable - Stock 1 module part number

23 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 23 Modular Inerting System

24 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 24 Modular Inerting System

25 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 25 Modular Inerting System Reduced weight over distributed components Removal of interstitial heater Fits within space availability of smaller aircraft One common designed component that is used across many aircraft

26 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES Health Monitoring

27 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 27 Health Monitoring System required to measure the health of the inerting system Options include: Measurement of O 2 in-tank Measurement of O 2 from inerting system Measurement of flow of NEA from inerting system

28 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 28 Health Monitoring Current oxygen sensors Test bed measurement of O 2 % in tank accomplished with FAA system Sensors have a short life Equipment requires large space availability Commercially available oxygen sensors cannot be placed in tank Sensing elements superheat sample, that may contain fuel vapors Measurement of O 2 % of NEA stream prior to tank infers tank O 2 % Purity of NEA produced by inerting system Should be used in conjunction with flow sensor Tight measurement tolerances required Failures in the following systems will not be detected NEA distribution Tank vent system Previous flight assumed inert

29 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 29 Health Monitoring Non-oxygen sensing methods Measure pressure or flow downstream of inerting system Latent hollow fiber membrane failures not detected Measure O 2 % of inerting system with GSE at lengthy intervals Tank O 2 % should be measured Tank O 2 level measured directly by sampling a few times during the flight at critical tank location Not inferred – total loop closure Can we reduce the life cycle costs of the inerting system?

30 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 30 Health Monitoring Current sensing methods are: Too large Not compatible with environment Flawed Currently working on developing system that will measure the O 2 % in-tank

31 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES Industry Standards

32 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 32 Industry Standards Industry standards are needed to define System performance System design

33 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 33 Industry Standards AIA Document Defines problem tanks Methods of defining flammability Sets flammability exposure limits Fleet wide average levels Special case of 80°F days Methods of reducing flammability Managing heat transfer Displacing the flammable zone Ullage sweeping Inerting Foam Monte Carlo Analysis Document submitted to FAA

34 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 34 Industry Standards SAE Group made up of cross-section from two SAE groups AE-5 Aerospace Fuel, Oil and Oxidizer Systems AC-9 Aircraft Environmental Systems Document encompases commercial and military aircraft Background Requirements System Design Validation & Verification

35 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 35 Industry Standards Background Lessons learned Gasses used Definition of inert Requirements Types of aircraft Fuels Environmental conditions

36 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 36 Industry Standards System Design Architectures Air sources Distribution methods Tank types Performance Impact to and from other systems System Control and monitoring Analysis methods Installation RMTS Validation & Verification

37 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 37 Industry Standards AIA document submitted to FAA SAE document currently in progress

38 © COPYRIGHT, PROPRIETARY INFORMATION OF SMITHS AEROSPACE LTD AND SHAW AERO DEVICES 38


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