FAA CLEEN

Cessna Citation Mustang · Performance

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Overview

This document, titled 'FAA CLEEN', provides performance data and insights related to the Cessna Citation Mustang, specifically focusing on the PW615F turbofan engine used in the aircraft. It outlines the engine's specifications, testing procedures, and alternative fuel evaluations. The document is intended for engineers, pilots, and aviation enthusiasts interested in the performance characteristics and advancements in engine technology for the Citation Mustang. Key topics include thrust ratings, emissions testing, and operational handling characteristics of the engine under various fuel types.

Cessna Citation Mustang uses PW615F engine with 1460 lbs thrust.
Engine features reverse flow combustor and dual-channel FADEC.
Testing includes emissions, particulates, and performance from ground idle to takeoff.
Alternative fuels being evaluated for performance and emissions impact.
FAA CLEEN goals include 20% fuel burn reduction and 60% NOx emissions reduction.

Document

Source

Originally published by www.faa.gov. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

View original at www.faa.gov

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Document details

Type: Performance
Year: 2012
Pages: 27
File size: 738 KB
Publisher: www.faa.gov

Documentation completeness

3/7

Most owners only have the POH. Here's the essential set for the Cessna Citation Mustang.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins
Type Certificate (TCDS)

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In this document

Engine Specifications

The Cessna Citation Mustang is equipped with the PW615F turbofan engine, which produces 1460 lbs of thrust. This engine features a reverse flow combustor and a dual-channel FADEC (Full Authority Digital Engine Control) system, ensuring efficient performance and reliability.

Testing Procedures

The document outlines a comprehensive test plan for the PW615F engine, which includes evaluating engine exhaust emissions, particulates, and performance characteristics such as specific fuel consumption (SFC) and thrust across various operational conditions, from ground idle to takeoff.

Alternative Fuel Evaluation

The document discusses the evaluation of alternative fuels for the PW615F engine, including blends of Jet A with various synthetic fuels. The testing aims to assess the impact of these fuels on emissions and overall engine performance.

Performance Characterization

Performance characterization tests will cover aspects such as acceleration and deceleration times, as well as the engine's response to negative fuel spikes, ensuring that the engine operates safely and efficiently under all conditions.

Environmental Impact Goals

The FAA CLEEN program aims to reduce fuel burn by over 20%, achieve a 60% reduction in NOx emissions compared to CAEP 6 standards, and lower noise levels by 25 EPNdB relative to Stage 4 noise regulations.

Full document text

FAA CLEEN November 2012 This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 2 Agenda • Geared Turbofan™ Engine Development & Certification Status • FAA CLEEN Technologies • Alternative Fuel Evaluation • FAA CLEEN Program Status This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 3 GTF Development & Certification Status This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 4 Customers Want: Lower Engine Cash Operating Cost Cost drivers • Fuel • Maintenance cost • Noise • Emissions • Reliability 20% Solution Geared Turbofan (GTF) This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 5 Efficiency of the fan to produce thrust Efficiency of the core to convert fuel into work Gearbox optimally integrates core & fan Fuel Efficiency ≈ propulsive efficiency x thermal efficiency Fuel Efficiency ≈ propulsive efficiency x thermal efficiency Fuel Burn Fan Diameter Noise Low Bypass Ratio Higher Fan Pressure Ratio High Bypass Ratio Lower Fan Pressure Ratio Low High Increasing weight of low-RPM LPT contributes to increasing fuel burn Advanced Turbofan (ATF) Better Geared Turbofan Engine (GTF) Fuel Burn Reduction Noise Reduction Gear enables higher performance LPT & fan GTF Engine Expands Design Space Paradigm Shift for Reduced Fuel Burn and Noise This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 6 PW1000G Engine Development Schedule Mature Engine Family 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 Development rig testing Validation rig testing Demonstration ground & flight testing CSeries & MRJ engine certification program FETT EIS cert A320neo family engine certification program FETT EIS cert design start design freeze This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 7 Program Status Next steps for 2012: • PW1100G-JM First Engine To Test • PW1500G engine certification Significant Testing Accomplished graph not to scale 2 engines 39 flights 400 hours 13 engines 3,300 hours 81 flights 415 flight hours 9,700 cycles This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 8 PW1500G flight test PW1500G Program Status 9 engines in test program: • 6 engines tested or at test • 3 engines in build  Bird strike testing  1000 endurance missions test  HPC thermal evaluation  2nd flight test engine program completed Extensive Testing Conducted to Date PW1500G ground test prep On track for 2012 certification This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 9 PW1200G flight test PW1200G Program Status • Block I testing completed all objectives • Successful flight test campaign • Supporting aircraft rig development for risk reduction • Aligning engine certification with aircraft certification PW1200G ground test Excellent test program to date This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 10 PW1100G-JM Program Status • Leveraging PW1200G and PW1500G experience • Excellent design progress • Last bolt ceremony held on October 26 (West Palm Beach) Engine for Airbus A320 Family of Aircraft On track for First Engine To Test in 2012 This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 11 PurePower PW1500G Benefits Fuel Burn >15% Noise Stage 4 – 20 dB NOx CAEP6 – 50% 33%* Stage 4 – 32 dB* CAEP6 – 60% PW1500G CLEEN Goals * Aircraft level This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 12 FAA CLEEN Technologies This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 13 FAA CLEEN Technologies Company Technology Goal Impact Projected Performance P&W Ultra-high bypass ratio Geared Turbofan w/ advanced fan system with reduced weight and drag Fuel-burn > 20% reduction Emissions 60% reduction in NOx (re: CAEP 6) Noise 25 EPNdB reduction (re: Stage 4) • UHB GTF technologies that leverage the overall GTF system benefits which we anticipate the market will demand in 2020 or beyond. • Alternate fuel evaluation task initiated in 2012 This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 14 FAA CLEEN TechnologyFuel Burn Fan Diameter Noise Low Bypass Ratio Higher Fan Pressure Ratio High Bypass Ratio Lower Fan Pressure Ratio Low High Increasing weight of low-RPM LPT contributes to increasing fuel burn Advanced Turbofan (ATF) Better Geared Turbofan (GTF) Fuel Burn Reduction Noise Reduction FAA CLEEN Demonstrator + additional technologies 0 5 10 15 20 25 30 0% 5% 10% 15% 20% 25% 30% Improving Noise Margin (cumulative decibels vs. Stage 4) Improving Engine Fuel Consumption Current engines Future GTF Models Vision Engine This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 15 Alternative Fuel Evaluation This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 16 FAA CLEEN – Alternative Fuel The baseline fuel and fuels to be tested from the three different processes are as follows: • Baseline Jet A (or Jet A-1) conforming to ASTM D1655 • 30/70 Kior HDCJ/Jet A • 50/50 Kior HDCJ/HEFA • 50/50 ARA CH/Jet A • 100% ARA CH • 50/50 Byogy/Jet A • 100% Byogy Kior Hydrotreated Depolymerized Cellulosic Jet (HDCJ) • Containing major content by volume of synthetic aromatics Applied Research Associates (ARA) Catalytic Hydrothermolysis (CH) • Containing intermediate content by volume synthetic aromatics Byogy renewables technology • Ethanol conversion into renewable jet fuel Alternative Fuel Blends For Demonstration Tests This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012

Show full text

J6949_FAA_CLEEN 17 FAA CLEEN – Alternative Fuel Engine Tests P&WC Turbofan Engine Model PW615F Selected • Cessna Citation Mustang currently in production • 1460lbs thrust, 2-spool turbofan engine • Reverse flow combustor, dual-channel FADEC • Test engine and facility available at P&WC Engine Test Plan Following tests to be completed for each test fuel • Engine exhaust emissions (gaseous species) • Engine exhaust particulates matters (LII & smoke number) • Engine performance characterization (SFC, Thrust) • Test points: Ground Idle to Takeoff • Basic engine operability handling – Accel and decel time check – Negative fuel spike (Lean blow-out margin) This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 18 FAA CLEEN – Alternative Fuel Combustor Rig Tests P&WC Generic Can Combustor Rig • P&WC combustor rig located at Laval University, Canada • Single nozzle can combustor rig design for generic research • Using representative fuel nozzle (JT15D) and ignitor (PW600) • Maximum air flow rate of 0.45kg/s (1 lb/sec) • Cold start capability; fuel and air (+35degC to -40degC) • Altitude relight (Sea level up to 50Kft or 15kPa) Combustor Test Plan Following tests to be completed for each test fuel • Cold start mapping at seal level constant pressure • Altitude relight mapping at constant speed (250 knots) This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 19 FAA CLEEN Program Status This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 20 FAA CLEEN Program Status • Technology plan in place • System studies show no major technical risks • Test engine identified • Close monitoring of NASA 22” fan rig Program on Track for Successful Completion Fan Rig Test (NASA) This Page Contains No Technical Data Subject to the EAR or the ITAR Nov 2012 November 8 2012 J6949_FAA_CLEEN 21 Test Asset Identified – Initial Flight Test Completed PW1500G Platforms PW1521G 21,000lbs CS100 CS300 PW1524G 23,300lbs PW1519G 19,000lbs CS100 Engine X806 Next test planned - acoustics This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 22 22” NASA Fan Rig Fan Rig Will Provide Early Learning for CLEEN Technologies • Complete set of pretest predictions completed • Fan system performance • Aeromechanic response • Operability mapping • Acoustics 2011 2012 2013 2014 2015 Fan Rig Studies Design Fab & Assy Grnd FAA/CLEEN Flt Design, Build & Test This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 23 Preliminary Design Nearing Completion • Fan structural and aero assessments completed • Nacelle configuration established Configuration selected that meets all criteria and satisfies FAA CLEEN goals This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 24 Preliminary Design Nearing Completion • Critical supplier quotes completed • Demonstration planning initiated – Ground / flight test matrix – Instrumentation requirements – FTB integration • Configuration Options – Fan Design – Nacelle Design BOM released Configuration selected that meets all criteria and satisfies FAA CLEEN goals • Evaluate – Performance – Operability – Acoustics This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 25 Combustor • Enhanced TALON X Core (HPC) • Increased OPR • Aero efficiency package Propulsor • High Bypass Ratio • Improved Propulsor Efficiency • Advanced Fan Drive Gear System Core (HPT) • Aero Efficiency Package • Physics Based Design and Lifing Systems LPT • Aero Efficiency Package 0 5 10 15 20 25 30 0% 5% 10% 15% 20% 25% 30% Improving Noise Margin (cumulative decibels vs. Stage 4) Improving Engine Fuel Consumption Current engines Future GTF Models Vision Engine FAA CLEEN Vision Engine This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 26 Summary • PW1000G family of engines demonstrating expected benefits of GTF architecture – Excellent foundation for achieving FAA CLEEN Goals • PW1500G engine ideal candidate for high bypass ratio technology demonstrator vehicle – FAA CLEEN identified asset completed flight testing – In preparation for acoustic testing • Alternative fuel engine & rig evaluation test plans defined • Critical CLEEN demonstrator hardware completing preliminary design – Supplier procurement in process • P&W progressing in maturing high bypass ratio technologies through ground & flight testing This Page Contains No Technical Data Subject to the EAR or the ITAR November 8 2012 J6949_FAA_CLEEN 27

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