-1- Cowling&ebu (cf6-80e1)

Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

1-P ower Pl ant  Nacelle

Overview The nacelle or cowling consists of the following components:     

Air intake cowls Fan cowl doors Thrust reverser cowl doors Core cowl doors Exhaust nozzle

In this lesson, you will learn about the location, identification, and purpose of the nacelle, and the components of the nacelle.

The nacelle is located under the wing of the aircraft, and is hinged to the pylon. The nacelle is divided into different components that are listed below. 1. The air intake cowls are at the front of the nacelle, forward of the fan cowl doors. 2. The fan cowl doors are installed aft of the air intake cowls. 3. The thrust reverser cowl doors are installed aft of the fan cowl doors. 4. The core cowl doors are installed aft of the thrust reverser cowl doors. 5. The exhaust nozzle is installed aft of the core cowl doors.

Nacelle purpose The nacelle provides smooth airflow in and around the engine. In addition, the nacelle provides access to the engine LRUs and cools the engine core. The nacelle also protects the engine components and isolates the engine from the airframe in case of an engine fire. Finally, the nacelle provides

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Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

openings for the engine drains and contains some of the thrust reverser components.

The air intake cowls Location: The air intake cowls are at the front of the nacelle, forward of the fan cowl doors. Identification: The air intake cowls are attached to the forward flange of the engine fan case. The cowls comprise the inlet lip and the forward and aft bulkheads. The inlet lip forms a smooth, cylindrical opening and is lined with special material that reduces the noise of air suction. The inlet lip also contains the anti-ice assembly. Purpose:    

Provides the engine fan with smooth airflow Directs the remaining airflow over the engine nacelle Prevents ice formation around the inlet lip Helps to reduce the noise of air suction

The fan cowl doors Location: The fan cowl doors are installed aft of the air intake cowls. Identification: The two fan cowl doors are hinged to the pylon. They are latched at the bottom centerline with three pressure relief latches that can be opened for accessing the engine components.

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Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

Purpose: The fan cowl doors provide a smooth, aerodynamic surface for unhindered airflow around the nacelle. They also provide access to various engine components.

The thrust reverser cowl doors Location: The thrust reverser cowl doors are installed aft of the fan cowl doors. Identification: The two thrust reverser cowl doors are hinged to the pylon at the top and are latched together at the bottom split line. The doors are designed to move along the pylon tracks. The thrust reverser cowl doors also house the components of the thrust reverser system. Purpose: The thrust reverser cowl doors form part of the thrust reverser system. When the thrust reverser is in the stowed position, the two thrust reverser cowl doors provide

a

smooth,

aerodynamic

surface for clean airflow around the engine. However, when the thrust reverser is deployed, the doors move aft along the pylon tracks thus providing space for the blocked airflow to escape. The doors can be opened to provide access to the engine and the thrust reverser components. A pressure relief door at the 6 o’clock position opens if the differential pressure between the nacelle air and the ambient air becomes greater than 3.5 psid.

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Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

The core cowl doors Location: The core cowl doors are installed aft of the thrust reverser cowl doors. Identification: There are two core cowl doors, both of which are hinged to the pylon. Purpose: In the closed position, the core cowl doors provide a smooth aerodynamic surface over the aft end of the engine core. In the open position, the doors provide access to the engine components.

The exhaust nozzle Location: The exhaust nozzle is installed aft of the core cowl doors. Identification: The exhaust nozzle is a convergent-divergent type of nozzle and consists of an exhaust sleeve and an exhaust plug. Purpose: 





Directs the engine exhaust gases overboard, thus providing the engine with nearly 20 % of the thrust. The exhaust sleeve releases low pressure recoup air and the drained fluids and vapors from the B and C sumps into the primary airflow stream. The exhaust plug vents the air/oil mixture from the sumps into the primary airflow stream.

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Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

 Engine Build Unit (EBU) Objectives Given an objective exercise, you will be able to:  Identify the location of the components of the engine build unit (EBU)  Identify the components of the engine build unit (EBU)  Identify the purpose of the components of the engine build unit (EBU)

Overview

The engine build unit (EBU) consists of the following systems and components:  Engine fire detection system  Engine bleed-air supply system  Hydraulic pumps  Integrated drive generator (IDG)  Engine air intake ice protection In this lesson, you will learn about the location, identification, and purpose of the systems, and components of the EBU.

Location Left Side View The CF6-80E1 engine build unit (EBU) consists of systems and components that are listed below.  The engine fire detection system is installed around the outer surfaces of the AGB and the upper and lower turbine areas in the core module.  The hydraulic pumps are installed on the forward side of the AGB.  The integrated drive generator (IDG) is installed on the aft side of the AGB.  The engine air intake ice protection system consists of components that are installed near the 11th compressor stage and in the lip assembly of the air intake cowls.

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Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

Location Right Side View The CF6-80E1 engine build unit (EBU) consists of systems and components that are listed below.  The engine bleed-air supply system components are installed in the nacelle and pylon of each engine.

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Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

Engine Fire Detection System Location: The engine fire detection system is installed around the outer surfaces of the AGB and the upper and lower turbine areas in the core module. Identification: The engine fire detection system has two continuous loops connected in parallel. Each loop has three fire detector

assemblies

and

the necessary wiring. The fire detector assembly consists of a sensor and a responder. Purpose: The engine fire detection system helps to detect and transmit information about an engine fire to the flight deck.

Engine Bleed-Air Supply System Location: The engine bleed-air supply system components are installed in the nacelle and pylon of each engine. Identification: The engine supply system consists of the following components:    

Ducts Intermediate pressure check (IPC) valve High pressure valve (HPV) Pressure regulating valve (PRV)

Purpose: The engine bleed-air supply system routes the air through a series of ducts for use by other aircraft systems. The ducting also allows bleed air from one engine to be routed to the other engine to aid in ground or air starting.

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Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

Hydraulic Pumps Location: The hydraulic pumps are installed on the forward side of the AGB. Identification: Each hydraulic pump is an engine-driven, variable displacement type unit. Purpose:

The

hydraulic

pump

supplies

hydraulic pressure to operate the different hydraulic systems of the aircraft.

Integrated Drive Generator Location: The integrated drive generator (IDG) is installed on the aft side of the AGB. Identification: The IDG has a constant speed drive (CSD) and an AC generator installed side by side in a single housing. The generator is a threephase and brushless rotating rectifier unit that is spray-oil cooled. Purpose: The IDG supplies 115-kva electrical power to the aircraft.

Engine Air Intake Ice Protection Location: The engine air intake ice protection system consists of components that are installed near the 11th HPC stage and in the lip assembly of the air intake cowls. Identification: The system consists of an anti-ice duct that gets bleed air from stage 11 of the HPC through the anti-ice valve. Purpose: The system sends hot air to the air intake cowls to prevent ice buildup on the lip assembly.

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Created by Rafik Chabou

ENGINE CF6-80E1

General Familiarization

Engine Build Unit Lesson Summary The engine build unit (EBU) consists of the following systems and components:  Engine fire detection system  Engine bleed-air supply system  Hydraulic pumps  Integrated drive generator (IDG)  Engine air intake ice protection The engine fire detection system helps in detecting engine fires. The engine bleed air-supply system supplies high-pressure bleed air to the aircraft. The hydraulic pumps supply hydraulic pressure for the operation of different aircraft systems and components. The IDG supplies electrical power to the aircraft. The engine air intake ice protection system makes sure that there is no ice formation around the air intake cowls.

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