Jt15d Ata 71 Intro

Pratt & Whitney JT15D Series (CAT C)

ATA 71-00 – INTRODUCTION

Page 1 of 10 FOR TRAINING PURPOSES ONLY © JT15D - ISSUE 1, 2009





0 TABLE OF CONTENTS

1 Introduction 3 1.1 Engines covered in this document 3 1.2 Abbreviations 4 2 JT15D-1/4 Series features 5 2.1 Main components 5 3 JT15D-5A/5D series features 7 3.1 Main components 7




1 INTRODUCTION

1.1 Engines covered in this document

Engine model Build Specification Number Certification Date Aircraft

JT15D-1 407 May 1971 Cessna Citation JT15D-1A 503 July 1976 Cessna Citation I JT15D-1B 623 July 1982 Cessna Citation I JT15D-4 412 September 1973 Aerospatiale Corvette JT15D-4 507 September 1973 Cessna Citation II JT15D-4 530 September 1973 Mitsubishi Diamond I JT15D-4B 638 May 1983 Cessna Citation Sll JT15D-4D 645 December 1983 Mitsubishi Diamond IA JT15D-5A 729 October 1988 Cessna Citation V JT15D-5D 810 December 1993 Cessna Citation V Ultra




1.2 Abbreviations

AGB - Accessory Gearbox BVC - Bleed Valve Controller FCU - Fuel Control Unit FDV - Flow Divider Valve Fn - Net thrust FOD - Foreign Object Damage HSI - Hot Section Inspection IBR - Integral Bladed Rotor ITT - InterTurbine Temperature (T5) LRU - Line Replaceable Unit N1 - Low pressure rotor speed N2 - High pressure rotor speed OAT - Outside Air Temperature PO - Bypass fuel Pressure P1 - Fuel pump Pressure P2 - Metered fuel Pressure P3 - Compressor discharge Pressure Pamb - Ambient Pressure (static) Px - Acceleration and enrichment pressure Py - Governor pressure TBO - Time Between Overhaul TSFC - Thrust Specific Fuel Consumption Wa - Engine Airflow Wb - Bypass duct airflow We - Core air flow Wf - Fuel flow




2 JT15D-1/4 SERIES FEATURES

Medium bypass turbofan engine

Twin Spool, the low and high pressure compressors are rotating on independent shafts and at different speeds

Reverse Flow takes place in the core gas path at the combustion chamber liner and the large exit duct area

Core Flow generates approximately 34% of engine thrust at sea level

Bypass Flow generates approximately 66% of engine thrust at sea level

2.1 Main Components

2.1.1 Compressors

1 stage axial low compressor (fan, D-1 series)

2 stage axial low compressors (fan + booster, D-4 series)

1 high compressor

Provide the necessary air pressure and flow to sustain combustion, cool hot section components and produce thrust

2.1.2 Combustion chamber

Annular

Reverse flow

Provide an area for the combustion of the air-fuel mixture




2.1.3 High Turbine

Single stage turbine, CW rotation

Provide the power to drive the high pressure compressor

2.1.4 Low Turbines

Two stage turbine CW rotation

Independent of high compressor turbine (free turbine)

Provide power to the low pressure compressor (fan + booster, D-4 series)

2.1.5 Accessory gearbox

Driven by high compressor

Provide drives for engine accessories

2.1.6 Engine control system

Hydro pneumatic Fuel Control Unit

Single lever power management

2.1.7 References JT15D-1/1A/1B

Thrust: 2200 Ibs Max engine airflow: 73.6 Ibs/sec Max bypass flow: 56.6 Ibs/sec Max core flow: 17.0 Ibs/sec Bypass Ratio: 3.3:1 Max compressor P/R: 8:1 Max TSFG: 0.540 Ib/hr/lbs thrust Length: 59 inches Diameter: 27 inches Dry Weight: 516 Ibs




2.1.8 References JT15D-4/4B/4D

Thrust: 2900 Ibs Max engine airflow: 77.8 Ibs/sec Max bypass flow: 56.6 Ibs/sec Max core flow: 21.2 Ibs/sec Bypass Ratio: 2.7:1 Max compressor P/R: 10.2:1 Max TSFC: 0.562 Ib/hr/lbs thrust Length: 60 inches Diameter: 27 inches Dry Weight: 557 Ibs

3 JT15D-5A/5D FEATURES

Medium bypass turbofan engine

Twin Spool, the low and high pressure compressors are rotating on independent shafts and at different speeds

Reverse flow takes place in the core gas path in the combustion chamber liner area

Core flow generates approximately 46% of engine thrust at sea level

Bypass flow generates approximately 54% of engine thrust at sea level

3.1 Main Components

3.1.1 Compressors

2 stages axial low compressor (fan + booster)

1 high compressor

Provide the necessary air pressure and flow to sustain combustion, cool hot section components and produce thrust




3.1.2 Combustion chamber

Annular

Reverse flow

Provide an area for the combustion of the air-fuel mixture

3.1.3 High Turbine

Single stage turbine, CW rotation

Provide the power to drive the high pressure compressor

3.1.4 Low Turbines

Two stage turbine CW rotation

Independent of high compressor turbine (free turbine)

Provide power to the low pressure compressor (fan + booster)

3.1.5 Accessory gearbox

Driven by the high compressor

Provide drives for engine accessories

3.1.6 Engine control system

Hydro pneumatic Fuel Control Unit

Electronically controlled bleed valve

Single lever power management




3.1.7 References JT15D-5A


3.1.8 References JT15D-5D





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Jt15d Ata 71 Intro