• Title/Summary/Keyword: Aircraft Engine Compressor Case

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Study on Deformation Analysis of Holes during Drilling of Aircraft Engine Compressor Cases (항공기 엔진 압축기 케이스의 드릴링 시 홀의 변형 해석에 관한 연구)

  • Park, Ki-Beom;Cho, Young-Tae;Jung, Yoon-Gyo
    • Journal of the Korean Society of Manufacturing Process Engineers
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    • v.17 no.3
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    • pp.65-70
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    • 2018
  • M152, used for aircraft engine compressor cases, causes many problems in the cutting process due to its high hardness and high toughness. Characterized by a concave cylindrical center, aircraft engine compressor cases are thin but have multiple side holes to connect with internal parts. Thus, deformation occurs despite the jig sustaining the inside. The object of this study was to lessen the deformation arising from drilling by improving the drilling jig for aircraft engine compressor cases. To this end, an aircraft engine compressor case modeled with SolidWorks was analyzed with ANSYS under real conditions. Then, to secure reliability, the analyzed deformation was compared with the actual deformation. Based on the results, the effects of the improved drilling jig for aircraft engine compressor cases were verified.

A Study on Engine Health Monitoring using Linear Gas Path Analysis for Turboprop Engine (선형 GPA 기법을 이용한 터보프롭 엔진의 성능진단에 관한 연구)

  • 공창덕;신현기;기자영
    • Journal of the Korean Society of Propulsion Engineers
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    • v.3 no.4
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    • pp.93-103
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    • 1999
  • The steady-state performance analysis program for turboprop engine which was used for a small, middle industrial aircraft and a basic trainer aircraft was developed and linear Gas Path Analysis method was applied to Engine Health Monitoring for Turboprop engine. This program was compared with TURBOMARCH program which is well known with performance and power according to flight Mach No. at the standard atmospheric condition to prove a steady-state performance analysis program. From the result, inlet, exit temperature and pressure of each component had error within 3% and especially power according to flight Mach No. had error within 2.4% so that this program could be assured. To make sure if linear Gas Path Analysis is reasonable four cases were selected. The first is the case that fouling is occurred in compressor only. The second is the case that fouling is occurred in compressor and erosion is occurred in turbine. The third is the case that erosion is occurred in both compressor and turbine and power turbine at the same time. Finally, the case that fouling and erosion are occurred in compressor, compressor turbine and power turbine was selected. Different parameters were selected impartially among the independent parameters so that the effect of measurement parameter selection was observed. From the result, the more measurement parameters the smaller RMS error and even though the number of measurement parameters was the same, the RMS error was obtained differently according to which measurement parameters were selected. The case using eight instrument parameters of case IV-4 had small error comparably and was economic and it was important to select optimal number of measurement and optimal measurement parameters.

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Numerical simulation of the unsteady flowfield in complete propulsion systems

  • Ferlauto, Michele;Marsilio, Roberto
    • Advances in aircraft and spacecraft science
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    • v.5 no.3
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    • pp.349-362
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    • 2018
  • A non-linear numerical simulation technique for predicting the unsteady performances of an airbreathing engine is developed. The study focuses on the simulation of integrated propulsion systems, where a closer coupling is needed between the airframe and the engine dynamics. In fact, the solution of the fully unsteady flow governing equations, rather than a lumped volume gas dynamics discretization, is essential for modeling the coupling between aero-servoelastic modes and engine dynamics in highly integrated propulsion systems. This consideration holds for any propulsion system when a full separation between the fluid dynamic time-scale and engine transient cannot be appreciated, as in the case of flow instabilities (e.g., rotating stall, surge, inlet unstart), or in case of sudden external perturbations (e.g., gas ingestion). Simulations of the coupling between external and internal flow are performed. The flow around the nacelle and inside the engine ducts (i.e., air intakes, nozzles) is solved by CFD computations, whereas the flow evolution through compressor and turbine bladings is simulated by actuator disks. Shaft work balance and rotor dynamics are deduced from the estimated torque on each turbine/compressor blade row.

A Study on Steady-State Performance Analysis and Dynamic Simulation for Medium Scale Civil Aircraft Turbofan Engine (I) (중형항공기용 터보팬엔진의 정상상태 성능해석 및 동적모사에 관한 연구 (I))

  • 공창덕;고광웅;기자영
    • Journal of the Korean Society of Propulsion Engineers
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    • v.2 no.2
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    • pp.47-55
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    • 1998
  • Steady-state and transient performance for the medium scale civil aircraft turbofan engine was analyzed. Steady-state performance was analyzed on maximum take-off condition, maximum climb condition, and cruise condition. At 90%RPM of the low pressure compressor, the partload performance was economized. The transient performance was analyzed with cases of the step increase, the ramp increase, the ramp decrease, and the step increase and ramp decrease for the input fuel flow. For the transient performance analysis, work matching between compressor and turbine was needed. Modified Euler method was used the integration of residual torque in work matching equation. At all flight condition, the overshoot of the high pressure turbine inlet temperature was appeared in the step and ramp increase case, and the surge of high pressure compressor was appeared in the step increase case and the ramp increase case within 5.5 seconds of maximum climb condition.

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Performance Analysis of the Propulsion System for the Combined Rotorcraft (복합형 로터항공기의 동력장치 성능해석 연구)

  • Jo, Hana;Choi, Seongman;Park, Kyungsu;Yang, Gyaebyung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.21 no.6
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    • pp.83-90
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    • 2017
  • Performance analysis of the turboshaft engines for combined rotorcraft was executed. A tip jet and a ducted fan aircraft were selected for combined rotorcraft application. Gasturb 12 software was used for turboshaft engine performance analysis. In the results, maximum required power for the tip jet engine is about 1,600 hp class and maximum required power for the ducted fan engine is about 1,000 hp class at the required aircraft mission. This is due to the additional power of the auxiliary compressor to get a bleed air mass flow rate for the tip jet operation. At the same time, fuel consumption of the tip jet aircraft is 2.8 times larger than ducted fan case. Therefore ducted fan type aircraft is more efficient than tip jet aircraft in terms of fuel economy.

Prediction of Erosion Rate in Passages of a Turbine Cascade with Two-Phase flow (터빈익렬 유로에서 2상 유동에 따른 삭마량 예측)

  • Yu, Man Sun;Kim, Wan Sik;Cho, Hyung Hee
    • 유체기계공업학회:학술대회논문집
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    • 1999.12a
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    • pp.301-308
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    • 1999
  • The present study investigates numerically particle laden flow through compressor cascades and a rocket nozzle. Engines are affected by various particles which are suspending in the atmosphere. Especially in the case of aircraft aviating in volcanic, industrial and desert region including many particles, each components of engine system are damaged severely. That damage modes are erosion of compressor blading and rotor path components, partial or total blockage of cooling passage and engine control system degradation. Numerical prediction and experimental data, erosion rates are predicted for two materials - ceramic, soft metal - on compressor blade surface. Aluminum oxide ($Al_2O_3$) Particles included in solid rocket propelant make ablative the rocket motor nozzle and imped the expansion processes of propulsion. By the definition of particle deposition efficiency, characteristics of particles impaction are considered quantitatively Stoke number is defined over the various particle sizes and particle trajectories are treated by Lagrangian approach. Particle stability is considered by definition of Weber number in rocket nozzle and particle breakup and evaporation is simulated in a rocket nozzle.

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Analysis of Particle Laden Flow and Erosion Rate Around Turbine Cascade (터빈 익렬 주위에서의 부유입자 유동 및 마모량 해석)

  • 김완식;조형희
    • Journal of the Korean Society of Propulsion Engineers
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    • v.2 no.2
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    • pp.14-23
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    • 1998
  • The present study investigates numerically particle laden flow through compressor cascade. In general, a lot of turbine engines are affected by various particles which are suspending in the atmosphere. Especially in the case of aircraft aviating in volcanic, industrial and desert region including many particles, each components of engine system are damaged severely. That damage modes are erosion of compressor binding and rotor path components, partial or total blockage of cooling passage and engine control system degradation.. Initial damages can not be serious but cumulation of damages influences on safety of aircraft control and economical maintenance cost of engine system can be increased. When dust, materials and volcanic particles in the atmosphere flow in the compressor, it is necessary to predict damaged and deposited region of compressor blades. To the various flow inlet angle, predictions of particles trajectory in compressor cascade by Lagrangian method are presented and impulses by impaction of particles at blade surface are calculated. By the definition of particle deposition efficiency, characteristics of particles impact are considered quantitatively. With these prediction and experimental data, erosion rates are predicted for two materials - ceramic, soft metal - on compressor blade surface. Improvements like coating of blade surface could be found, by above prediction.

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Automatic Generation of CAM Model for Machining Holes for Jet Engine Compressor Case Based on Feature Recognition (제트엔진 압축기 케이스의 구멍 가공을 위한 특징형상 인식 기반의 CAM 모델 자동생성)

  • Kim, Byung Chul;Song, Ilhwan
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.39 no.3
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    • pp.337-345
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    • 2015
  • High machining technology is needed for manufacturing jet engines for use in aircrafts. To reduce errors in the jet engine machining process, the machining companies of aircraft engines have introduced the CAM (computer-aided manufacturing) technology. However, to create a CAM model, the operator must manually conduct machining operations based on a CAD (computer-aided design) model, which can take several days or weeks. To solve this problem, this study proposes a method for automatically generating a CAM model for machining holes in the parts, using a CAD model. In this method, the features of the hole are recognized from the CAD model and translated into machining operations to be used with the CATIA program. Additionally, a prototype system was implemented and the proposed method was experimentally verified.

A Fast Generation Method of CAM Model for Machining of Jet Engines Using Shape Search (형상 검색을 이용한 제트엔진 절삭가공을 위한 빠른 CAM 모델 생성 방법)

  • Kim, Byung Chul;Song, Ilhwan;Shin, Suchul
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.40 no.3
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    • pp.327-336
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    • 2016
  • Manufacturers of aircraft engines have introduced computer-aided manufacturing (CAM) software to operate and control computerized numerical control (CNC) machine tools. However, the generation of a CAM model is a time consuming and error-prone task since machining procedure and operational details are manually defined. For the automatic generation of a CAM model, feature recognition techniques have been widely studied. However, their recognition coverage is limited so that complex shapes such as a jet engine cannot be fully developed. This study presents a novel approach to quickly generate a CAM model from a CAD model using shape search techniques. Once an operator sets a machining operation as a reference operation, the same shapes as the shapes referenced by the operation are searched. The reference operation is copied to the positions of the searched shapes. The proposed method was verified through experiments with a jet engine compressor case.

A Study on Defect Diagnostics of Gas-Turbine Engine on Off-Design Condition Using Genetic Algorithms (유전 알고리즘을 이용한 탈 설계 영역에서의 항공기용 가스터빈 엔진 결함 진단)

  • Yong, Min-Chul;Seo, Dong-Hyuck;Choi, Dong-Whan;Roh, Tae-Seong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.3
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    • pp.60-67
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    • 2008
  • In this study, the genetic algorithm has been used for the real-time defect diagnosis on the operation of the aircraft gas-turbine engine. The component elements of the gas-turbine engine for consideration of the performance deterioration consist of the compressor, the gas generation turbine and the power turbine. Compared to the on-design point, the teaming data has been increased 200 times in case off-design conditions for the altitude, the flight mach number and the fuel consumption. Therefore, enormous learning time has been required for the satisfied convergence. The optimal division has been proposed for learning time decrease as well as the high accuracy. As results, the RMS errors of the defect diagnosis using the genetic algorithm have been confirmed under 5 %.