Analysis of Operational Characteristics of Aviation Dieseland Gas Turbine Engines for Light Passenger Aircraft

Loginov, Vasyl; Ukraintes, Yevgeniy

doi:10.5604/05096669.1226429

Cited by 4 publications

(5 citation statements)

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“…As is known, when a power plant is placed on a wing, the lift force of the «power plant-wing» system changes and depends on the type of engine [16,17].…”

Section: The Study Materials and Methodsmentioning

confidence: 99%

Design of the parametric appearance of the power plant for modifications of the regional passenger aircraft An-158

Loginov,

Ukrainets,

Humennyi

et al. 2023

EEJET

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The object of research is the process of remotorization of a regional passenger aircraft to increase its fuel efficiency. Based on the conceptual requirements for the remotorization of the An-158 aircraft with turbojet bypass engines, a parametric appearance of three modifications of this aircraft with turboprop engines for 80, 100, and 120 passenger seats was formed. The study was carried out on the basis of the well-known modular software systems «Integration 2.1» and «Air propeller 2.2» for typical flight profiles of the An-158 aircraft. Improved procedures of weight design and determination of the takeoff characteristics of aircraft with different types of power plant engines have made it possible to identify the most advantageous flight speeds of aircraft modifications with a turboprop engine corresponding to different flight masses. The results of the study of flight performance for optimal and «non-optimal» modifications of the aircraft are reported. The parametric appearance of the propeller was formed, the shape of the propeller blade for the cruising flight mode was determined for modifying the aircraft with a maximum number of passengers – 120 people. It is shown that the propeller for this modification of the aircraft cannot have less than 8 blades since with a smaller number of blades, the maximum chord of the propeller blade increases. The inductive power costs increase significantly due to the small elongation of the blades and, as a result, the flight efficiency of the propeller decreases. It is shown that the total fuel consumption for the entire typical flight of all modifications of the aircraft with turboprop engine at all studied flight speeds is less than the total fuel consumption of the An-158 base aircraft

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“…As is known, when a power plant is placed on a wing, the lift force of the «power plant-wing» system changes and depends on the type of engine [16,17].…”

Section: The Study Materials and Methodsmentioning

confidence: 99%

Design of the parametric appearance of the power plant for modifications of the regional passenger aircraft An-158

Loginov,

Ukrainets,

Humennyi

et al. 2023

EEJET

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“…We studied a chosen group of civil light turboprop aircraft based on a classical aerodynamic scheme, with a horizontal tail in the tail part of fuselage, with take-off weight from 2,200 to 5,700 kg and with payload from 600 to 2,000 kg. The aerodynamic schemes of the following light aircraft of the studied type were chosen for the analysis: Cessna 441 Conquest II [17], Cessna 425 Corsair, Commander Jetprop 840 [18], EMB-121 Xingu, Merlin IIIB [20], Mu-2B-60 Marquise [21], PA-42 Cheyenne III, Beech Model 200 Super King Air, King Air F90, Cessna Caravan [19], TBM-850, Rysochok [17], Piaggio P-166, M 101T Gzhel, CM-92 T Turbo-Finist, Piper Cheyenne I (PA-31T-500I), Piper Meridian 500 [23], and A-viator [4,6,14,15,17,22]. Based on the Technical Requirements Specification and analysis of the parameters and characteristics of prototype aircraft [17], the concept for creating a new competitive KhAI-90 civil light aircraft was developed and the basic tactical and technical requirements (TTR) were identified.…”

Section: Analysis Of Parameters and Characteristics Of Prototype Aircraftmentioning

confidence: 99%

“…A "light civil aircraft" is a multi-purpose category with a number of seats, excluding pilots, not more than nine, with a maximum certified take-off weight of not more than 5,700 kg [13,14]. Comparative analysis of 5-to 19-seater aircraft has shown the economic viability of using gas turbine aircraft engines use for airplanes of local airlines (carrying 5-6 passengers) [15]. The evolution of the basic parameters and characteristics of such aircraft, involving the continual complication and detailed elaboration of their structure, the aerodynamic, internal and load-charring layout of units, systems and equipment, is described shown in [1,16].…”

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confidence: 99%

The KhAI-90 Light Civil Turboprop Airplane Pilot Project

Grebenikov

Loginov²,

Humennyi

et al. 2021

Transactions on Aerospace Research

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The pilot project of new light civil turboprop aircraft, called the KhAI-90, featuring a cruising speed of 350km/h, payload of 600 kg at 500 km range, and equipped with two turboprop Rolls-Royce 250-B17F engines each with power of 420 hp (alternatively, two AI-450C engines each with power of 450 hp may be installed) is presented herein. Based on the developed technical task, the concept for creating the KhAI-90 new competitive light civil aircraft, and the analysis of prototypes’ aircraft parameters and characteristics, the main tactical and technical requirements are assigned. The take-off weight of the new aircraft is determined in three approximations at the preliminary design stage of light civil turboprop aircraft, using the iterative software “CLA-TOW”, studying the influence of the wing geometric parameters and lift devices on aerodynamic performance, the power-to-weight ratio and the airplane weight parameters. The following parameters are calculated for the design: minimum take-off weight WTO min = 3,600 kg, optimal wing loading p 0 opt = 130 daN/m2, optimal aspect ratio 9.6, taper ratio 2.25, sweep angle at leading edge 3 degrees, airfoil relative thickness 10.6%. A general view and three-dimensional parametric models of the master-geometry and passenger cabin space distribution are constructed for the KhAI-90 by means of the SIEMENS NX computer integrated system. More broadly, this pilot project has also demonstrated the viability of the method we developed and previously reported for determining light civil turboprop airplane parameters.

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“…We studied the characteristics of a long-range heavy aircraft under conditions of a typical flight profile using the developed modular software complex «Integration-2.1» (Fig. 3, 4), based on the methodology outlined in works [35][36][37].…”

Section: Procedures For Studying a Change In The Aerodynamic Quality And Fuel Efficiency When Considering The Aircraft Flight Rangementioning

confidence: 99%

Improving aircraft fuel efficiency by using the adaptive wing and winglets

Popov¹,

Loginov

Ukrainets

et al. 2020

EEJET

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Підвищення паливної ефективності літа ка є однією із основних вимог, які висувають ся до перспективних літальних апаратів та літальних апаратів, які модернізуються. Проведено оцінку зміни аеродинамічної якос ті і, як наслідок, підвищення паливної ефек тивності дальнього магістрального літака при застосуванні перспективних засобів під вищення аеродинамічної якості. До зазначе них засобів відносяться: відмова від меха нізації кромок крила та від традиційних органів керування шляхом застосування адаптивного крила, штучна ламінарізація течії навколо елементів планеру, застосу вання кінцевих аеродинамічних поверхонь. Відмова від традиційних органів керуван ня та механізації крила зумовлена необхід ністю забезпечення безшовної поверхні еле ментів планера для запобігання передчасної турбулізації течії і, як наслідок, призво дить до зменшення профільного опору літа ка. Застосування кінцевих аеродинамічних поверхонь направлене на зниження індук тивного опору. Визначення зміни паливної ефективності літака дозволить оцінити зміну його експлуатаційних витрат протя гом життєвого циклу. Дослідження проведено на основі відомо го модульного програмного комплексу «Інте грація 2.1». Інженерноштурманський роз рахунок виконувався для типового профілю польоту дальнього магістрального літака. Показана можливість зменшення витрати палива до 20 %. Найбільший вплив на зменшен ня витрати палива має ламінарізація течії на поверхні елементів планеру, при цьому зменшення витрати палива склало 17,1 %. Відмова від механізації та елеронів забезпе чила зменшення витрати палива на 3,9 %, при цьому відмова від елеронів, передкрилка та закрилка забезпечило зменшення витра ти палива на 0,4, 1,5 та 0,4 відсотків від повідно. Застосування спіроідних кінцевих аеродинамічних поверхонь забезпечило змен шення витрати палива на 1,95 % Ключові слова: аеродинамічна якість, паливна ефективність, адаптивне крило, штучна ламінарізація, спіроідні кінцеві аеро динамічні поверхні UDC 629.7.

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Analysis of Operational Characteristics of Aviation Dieseland Gas Turbine Engines for Light Passenger Aircraft

Cited by 4 publications

References 1 publication

Design of the parametric appearance of the power plant for modifications of the regional passenger aircraft An-158

Design of the parametric appearance of the power plant for modifications of the regional passenger aircraft An-158

The KhAI-90 Light Civil Turboprop Airplane Pilot Project

Improving aircraft fuel efficiency by using the adaptive wing and winglets

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