Analiza perfomansi koncepcije mlaznih motora visokog stupnja optočnosti

undergraduate thesis

• Title (english): Performance Analysis of the Turbofan Engine with High By-Pass Ratio
• Author: Danijel Horvat
• Mentor: Anita Domitrović (mentor)
• Committee member: Željko Marušić (predsjednik povjerenstva)
• Committee member: Karolina Krajček Nikolić (član povjerenstva)
• Committee member: Tino Bucak (član povjerenstva)
• Granter: University of Zagreb; Faculty of Transport and Traffic Sciences; (Division of Aeronautics); (Department of Aeronautics); Zagreb
• Defense date and country: 2016-09-13, Croatia
• Scientific / art field, discipline and subdiscipline: TECHNICAL SCIENCES; Traffic and Transport Technology; Air Traffic

Abstract

Uvođenjem reduktora u konstrukciju mlaznih motora s visokim stupnjem optočnosti koji se nalazi između ventilatora i niskotlačnog kompresora omogućuje da se svaki modul (ventilator, niskotlačni kompresor i niskotlačna turbina koja ga pogoni) vrte svojom optimalnom brzinom vrtnje. Za veću efikasnost propulzije ventilator ima manju brzinu vrtnje dok se niskotlačni kompresor i turbina vrte većim brzinama od konvencionalnih mlaznih motora sa visokim stupnjem optočnosti čime se povečava učinkovitost motora.
Smanjenjem brzine vrtnje ventilatora smanjuje se buka motora, korištenjem napredne tehnologije u izradi i dizajnu komore izgaranja treće generacije TALON X, te naprednim dizajnom lopatica turbine koje učinkovitije pretvaraju energiju ispušnih plinova u mehanički rad smanjena je potrošnja goriva i emisije ispušnih plinova. Većom brzinom vrtnje jezgre motora (kompresora i turbine) povećana je njihova učinkovitost koja dozvoljava manji broj stupnjeva kompresora i turbine ćime se smanjuju troškovi održavanja i masa motora. U ovom radu analiziraju se performanse i tehničke specifičnosti nove generacije motora sa vrlo visokim stupnjem optočnosti PW1100G-JM i uspoređuju se sa konvencionalnim motorom visokog stupnja optočnosti CFM56-5A1.

Abstract (english)

Introducing reduction gear in the design of high bypass turbofan jet engine which is placed between fan and low pressure compresor, enables for each module (fan, low pressure compresor and low pressure turbine which drives it) to rotare at optimum speed. For achieving higher propulsive efficiency, rotation speed of fan is reduced and rotation speed of low pressure compresor and it's turbine is increased compared to conventional high bypass turbofan engine enabling higher engine efficiency.
Engine noise is reduced by reducing rotational speed of fan, introducing new technology in manufacturing and design of third generation combustor TALON X and advanced design of turbine blades which are more efficient in converting gas energy in mechanical work, engine consumption and exhaust gas emissions are reduced. Engine core efficiency (compressor and turbine) is increased by increasing it's speed of rotation, therefore required stages in compresor and turbine are reduced which reduces maintenance cost's and mass. In this paper there are comparison of the performance and technical specification between new generation of the ultra high bypass ratio turbofan engine PW1100G-JM and conventional high bypass turbofan engine CFM56-5A1.

• Keywords: mlazni motor visokog stupnja optočnosti; reduktor; učinkovitost; napredna tehnologija; potrošnja goriva
• Keywords (english): high bypass ratio turbofan engine; reduction gear; efficiency; advanced technology; fuel consumption
• Language: croatian
• URN:NBN: urn:nbn:hr:119:728041
• Study programme: Title: Aeronautics; Study programme type: university; Study level: undergraduate; Academic / professional title: sveučilišni/a prvostupnik/prvostupnica (baccalaureus/baccalaurea) inženjer/inženjerka aeronautike (sveučilišni/a prvostupnik/prvostupnica (baccalaureus/baccalaurea) inženjer/inženjerka aeronautike)
• Type of resource: Text
• File origin: Born digital
• Access conditions: Open access
• Created on: 2016-09-19 13:24:18