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Engine Assemblies

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by

Mayur Kumar

on 8 September 2014

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Transcript of Engine Assemblies

ADOUR MK 811/871
Rolls-Royce Turbomeca Adour
twin spool low by-pass turbofan engine
primarily developed to power the JAGUAR AIRCRAFT.
It consists of a 2 stage LP compressor and 5 stage HP compressors.
Compressors are driven by separate single stage turbines driven by co-axial shafts with low pressure shaft passing through high pressure shaft.
Air Inatke Duct:bolted to air intake casing
Air Intake Casing:directs air into compressor etc.
Compressor:7 stage axial flow compressor
Compressor Casing:two halves of alloys bolted together
Compressor Rotor & Turbine Shaft:comprises of rotor blades,discs and spacing rings
Delivery Casing:bolted to rear of compression casing
Combustion Chamber:7 seprate combustion chambers
Turbine:consists of turbine wheel assembly with blades having fir tree roots
a. Air intake casing containing reduction gear
b. Compressor front casing
c. 2nd stage compressor and main casing
d. Compressor outlet casing
e. Combustion chamber
f. Turbine section
g. Exhaust

In-Plant Training
ENGINE ASSEMBLIES
ENGINE DIVISION HAL BANGALORE

PRESENTED BY:
MARINA JOBAIE(46)
AKSHAY ARYA(01)
ANSHUL SAIWAL(04)

MODULES OF ADOUR ENGINE 811
MODULAR PARTS:
Module 01 LP Compressor Assembly
Module 02 LP Compressor Outlet Guide Vanes
Module 03 Intermediate Case
Module 04 HP Compressor Assembly
Module 05 HP Turbine NGV Assembly
Module 06 HP Turbine & Shaft
Module 07 LP Turbine NGVs & Turbine Bearing Assembly
Module 08 LP Turbine & Shaft
Module 09 Exhaust Unit & Mixer
Module 10 External Gearbox
Module 11 Oil Tank,Filters & Oil Cooler
Module 12 Afterburning Manifold Assembly

NON MODULAR PARTS:
Air Intake Fairing
Combustion Outer Case
Combustion Section
ORPHEUS ENGINE
turbojet engine with 7 stage axial compressor and single stage turbine.
has can-annular type combustion chamber.
used in the production of Kiran mark II.


Type of engine: Straight flow turbojet
Arrangement: 7 stage axial compressor and single
stage turbine
Rotation: ACW
Overall weight: 33.855 in.
Combustion system: straight flow annular casing
with 7 separate combustion chambers
Turbine: single stage axial flow
Stator: 63 blades
Rotor: 125 blades
CONSTRUCTION
Rolls-Royce Dart -a propeller turbine aero engine
has two-stage Centrifugal Compressors, three- stage Turbine
a can type combustion chamber and utilises water methanol injection to increase the shaft Horse Power.
compressor directly coupled to turbine and propeller driven from turbine through a compound reduction gear.
installed on Hawker Siddeley HS 748.

Type : turboprop
Compression ratio : 5.62:1
Combustion chamber : can type combustion chamber
(7 cans)
Turbine : 3 stage
Power : 1835 shp

DART ENGINE
GARETTE TPE331-a turboprop engine utilizing two stage centrifugal compressor, an annular combustion chamber and a three stage axial turbine with integral gearbox.
horsepower ratings vary from 575 to 1250 shaft horsepower depending on engine model and installation.
features a propeller control system, anti-icing and foreign object damage resistance, reverse thrust and negative torque sensing facilities.
used to power DORNIER AIRCRAFT.
GARRETT ENGINE
• Type : turboprop
• Compression ratio : 10.5
• Combustion chamber : annular
• Gas generator rpm : 41,370
• Power : 715 shaft horse power
• Specific fuel consumption : 0.590 lb/hr/shp
• Time before overhaul: 3600hrsWeight (kg) – 164
• Specific Fuel Consumption - 0.268 (kg / shp-hr)

CONSTRUCTION AND LEADING PARTICULARS
Centrifugalcompressor : compression ratio of 10:1 & airflow of 7.5 airflow per second

Combustor:annular type

3rd stage turbine:3 stage axial turbine

Gas generator:at 100% speed gas generator operates at 41,730 rpm

ARTOUSTE III-a turbo shaft of fixed engine type with drive shaft in front.
used in CHEETAH-CHETAK HELICOPTERS.
has 1750 flying hours before servicing
has side air intake, one axial and one centrifugal compressor connected to a three-stage Turbine
power output is 550 SHP at 33500 RPM. The reduction Gearbox in the front transfers the power to Helicopter.
More than 665 Engines have been manufactured and 2950 Engines overhauled and repaired for various Customers.
ARTOUSTE ENGINE
• Maximum Diameter (m) - 0.50
• Length (m) - 1.815
• Weight (kg) - 182
• Power - 550
• Specific Fuel Consumption
(Kg / shp-hr) - 0.346
• Turboshaft
• Compression Ratio : 5.2:1
• Combustion Chamber : Annular
• Engine Rpm : 41,370
• Power : 550 Shp
• Specific Fuel Consumption : 0.346 Lb/Hr/Shp
• Time Before Overhaul : 1750hrs
• Aircraft : Cheetah And Chetak Helicopters


FRONT SECTION : Reduction gear, Output Shaft & Accessory Drive

GAS GENERATOR : Air Intake , Axial Compressor , Centrifual Compressor,turbine & Combustion chamber


LEADING PARTICULARS
CONSTRUCTION
TM333 2B2-a free turbine turbo shaft engine.
found its first commercial application on the HAL Dhruv helicopters under Mach 3 and 4.
consists of an annular air intake, 2 stage axial compressor, single stage centrifugal compressor, annular reverse flow combustion chamber and a single stage axial turbine, power turbine and exhaust pipe.
TM333 2B2 ENGINE
• Type : Free turbine turbo shaft engine
• Combustion chamber: Annular
• Concept : Modular ( 01 & 02)
• Maximum take-off power: 825 KW
• Specific fuel consumption : 0.323 Kg/ KW – hr
• Compression ratio : 10:1
• Air-fuel ratio: 45:1
• Air mass flow: 3.1 Kg/s
• Gas generator speed: 45000 rpm (ACW)
• Power turbine speed: 37562 rpm (CW)
• Output shaft speed: 6000 rpm(ACW)
• Oil consumption: 0.3L/hr
• Maximum oil pressure: 800 Kpa
• Maximum oil temperature: 115 degrees Celsius
• Mass: 167 Kgs
• Time before overhaul : 1250hrs
• Aircraft : ALH Dhruv

CONSTRUCTION & LEADING PARTICULARS
While TM 3332B2 has 2 modules Shakti engine has 3 modules as given below:

Mod 01 Reduction Gear

Mod 02 Gas Generator

Mod 03 Power Turbine
Gnome-a turbo shaft single spool and free power turbine type engine
used in search and rescue helicopters and has anti-submarine warfare applications.
installed on Westland Sea King helicopters.
GNOME ENGINE
* Type: turbo shaft
* Compression ratio: 8.1:1
* Combustion chamber: annular
* Turbine: 2 stage
* Engine rpm: 27,100
* Power: 1380 shp
* Specific fuel consumption: 0.633 lb/hr/shp
* Time before overhaul : 1600
* Aircraft : Sea king helicopters
* Max. contingency : 1460 hp for 2.5 minutes
* Max. rating : 1380 h.p for 1 hr
* Max. continuous: 1050 h.p

LEADING PARTICULARS
THANK YOU!!
KIRAN MK - II
Leading particulars-
• Type of propulsion unit – Rolls Royce, Turbofan, Variable reheat bypass engine.
• Without afterburning : 5620 lbf
• With afterburner : 8400 lbf
• Direction of rotation of shafts : anti-clockwise (viewed from rear)
• By-pass ratio : 0.74 : 1
• Compression ratio : 11.3 : 1
• Oil consumption : 0.57 litres/hr
• Engine max. rpm : h.p 104% - 16132 ; l.p 104% - 14144
• Time before overhaul : 1200 flying hours
• Specific Fuel Consumption – 0.80 (kg / kg-hr)

JAGUAR AIRCRAFT
EXPLODED VIEW
EXPLODED VIEW
CONSTRUCTION
HS- 748 AVRO AIRCRAFT
CONSTRUCTION
EXPLODED VIEW
DORNIER DO-228 AIRCRAFT
EXPLODED VIEW
CHETAK / CHEETAH HELICOPTER
EXPLODED VIEW
HAL DHRUV HELICOPTER
SHAKTI ENGINE
MODULE 1 - Reduction Gear Box
MODULE 2- Gas Generator
EXPLODED VIEW
The shakti series engines have a radial air intake and a two-stage centrifugal compressor driven by a single stage axial gas generator turbine. Airflow is directed through a reverse flow annular combustion chamber, through the gas generator turbine and then through and a two-stage axial free power turbine. Output power is transmitted to a front-mounted reduction gearbox by a shaft concentrically mounted within the gas generator rotor assembly. The accessory gearbox, also mounted at the front end, is driven by the gas generator.
LIGHT COMBAT HELICOPTER
CONSTRUCTION & LEADING PARTICULARS
•Type : free turbine turbo shaft engine
Combustion chamber: Annular reverse flow
• Maximum take-off power: 1032 KW
• Specific fuel consumption : 0.323 Kg/ KW – hr
• Compression ratio : 12.7:1
• Air-fuel ratio: 45:1
• Air mass flow: 3.1 Kg/s
• Gas generator speed: 39598 rpm (CW)
• Power turbine speed: 20889 rpm (ACW)
• Output shaft speed: 6000 rpm(CW)
• Oil consumption: 0.3L/hr
• Maximum oil pressure: 900 Kpa
• Maximum oil temperature: 110 degreesCelsius
• Mass: 200 Kgs
• Time before overhaul : 1250hrs

EXPLODED VIEW
SEAKING HELICOPTER
EXPLODED VIEW
Full transcript