Set Of Blades Research Articles

Mistuning sensitivity and optimization for bladed disks using high-fidelity models

Abstract An effective method is developed for efficient calculations of the sensitivity of the maximum forced response levels for mistuned bladed disks with respect to blade frequency mistuning. The expressions for 1st and 2nd order sensitivity coefficients are derived in an analytical form which provides high accuracy and computational efficiency. Then, the optimization methods are used for searching the best and worst mistuning patterns of bladed disks. Two major types of the mistuning optimization problems are considered: (i) a continuous optimization problem when the blade mistuning can take any values from a prescribed range and (ii) a combinatorial optimization problem, when the set of mistuned blades is given and the optimization can be achieved by blade re-arrangement in a disk. For the first type of the optimization problem a set of sensitivity-based optimization algorithms is applied and for the second type a variant of a genetic algorithm is developed. The analysis of mistuning sensitivity coefficients and results of optimization searching are shown on an example of a realistic turbine bladed disk.

Non-Empirical BEM Corrections Relating to Angular and Axial Momentum Conservation

The Blade-Element Momentum (BEM) model for Horizontal-Axis Wind Turbines (HAWTs), although extremely useful, is known to be approximate due to model formulation insufficiencies, for which add-ons and corrections have been formulated over the past many decades. Scrutiny of the axial and azimuthal momentum conservation properties reveals momentum simplifications and absence of momentum sources not included in momentum theory underlying the standard BEM. One aspect relates to azimuthal momentum conservation, the wake swirl. This correction can be expressed analytically. Another aspect relates to axial momentum conservation, the wake expansion. This correction is not analytically quantifiable. The latter correction term is therefore quantified from postprocessing a large number of axisymmetric Actuator Disk (AD) Navier-Stokes computations with systematic variation of disk loading and tip-speed ratio. The new momentum correction terms are then included in the BEM model, and results benchmarked against references. The corrected BEM is derived by re-visiting the governing equations. For a disk represented by a constant-circulation set of blades, the corrected BEM contains no approximation to the underlying conservation laws. The study contributes by bridging the gap between BEM and the axisymmetric AD method for all disk load levels and tip speed ratios relevant for a wind turbine. The wake swirl correction leads to higher power efficiency at lower tip-speed ratios. The wake expansion correction causes a redistribution of the potential for power extraction, which increases on the inner part of the rotor and decreases on the outer part of the rotor. The overall rotor-averaged value of Betz limit is unaffected by the new corrections, but exceeding Betz locally on the inner- and mid-section of the rotor is shown to be possible. The two corrections significantly improve the axi-symmetric static BEM modelling accuracy for the radial distributions as well as for the rotor-integrated quantities, by reducing errors, approximately one order of magnitude. The relevance of these corrections for modern multi-MW rotors is quantified and discussed.

Reliability Analysis of Aero-Engine Compressor Rotor System Considering Cruise Characteristics

This paper develops an improved dynamic reliability model for compressor rotor system, defined as a “unconventional active system” here. First, regarding to the variety of system-component connections, system specific reliability modeling technique is presented, in which the stress and strength are both nonnegative stochastic processes. The new model fully considers the load characteristics of rotor blades, and inherently embodied the effect of the statistical dependence between the failures of the rotor blades. Then, calculated by the new model, the relationship between reliability and time, and that between the hazard rate and time, for a compressor rotor system are discussed, respectively. Comparing to the traditional series system reliability model, the new system reliability model developed in this paper has higher accuracy for compressor rotor system, since the traditional models neglect the difference between compressor rotor system and traditional active system. Moreover, in order to master the cruise characteristics of the aero-plane during reliability analysis of its compressor rotor blade set, a flight cruise is separated into several stages based on the value of Mach number and its change rate, and a subsection solution method is innovatively proposed accordingly. At the end of the paper, a certain cruise of fighter plane is analyzed to verify the accuracy of the new method. The results show that, as to a flight cruise with different stages, the new method is basically reasonable to most of the load histories, especially for the situation with impact loads existing.

Investigation of flow kinematics in the structured multibed catalytic cartridge

The reduction of harmful substances emission into the atmosphere is very important to create compact, energy-efficient catalytic units for afterburning volatile organic compounds. A key component of such units is the catalyst cartridge. The efficiency of its operation is provided by the supply of a gas flow with a uniform velocity field. To solve the problem, the gas flow distributor and an aerodynamic stand for its testing were created. A set of air-flow blades was used to align the velocity profile before the catalyst cartridge. Also flow kinematics inside the cartridge was investigated via laser Doppler anemometry method.

Multiobjective Optimization Design and Experimental Investigation on the Axial Flow Pump with Orthogonal Test Approach

A multiobjective optimization technique based on the computational fluid dynamics (CFD) simulations and the orthogonal test is proposed to reduce the pressure pulsation in this paper. Three levels of four well‐known performance factors L9 (34) were considered in the orthogonal test scheme: the number of blades, the blade setting angle, the hub ratio, and the distance between the blade and the guide vane. The evaluation indexes corresponded to the head, efficiency, shaft power, and pressure pulsation, respectively. An optimal configuration A2B1C2D3 was obtained by comprehensive frequency analysis method, after intuitive and range analysis. In comparison with the nonoptimized model, the new design’s head and efficiency increased by 17.8% and 4.26%, whilst the shaft power and the pressure pulsation coefficient reduced by 1.22% and 11%, respectively. Experiments conducted on the optimized pump were consistent with the CFD model. Six different rotational speed conditions in the optimal operating points were numerically calculated in order to explore the internal hydraulic characteristics of the optimized axial flow pump. It is verified that the comprehensive frequency analysis method based on the orthogonal test approach is effective for the multiobjective optimization of the axial flow pump.

Performance Testing of an Axial Flow Fan Designed for Air-Cooled Heat Exchanger Applications

An axial flow fan developed in the previous study is tested in order to characterize its performance. The M-fan, a 7.3152 m diameter rotor only axial flow fan was designed to perform well under the challenging operating conditions encountered in air-cooled heat exchangers. Preliminary computational fluid dynamics (CFD) results obtained using an actuator disk model (ADM) as well as a periodic three dimensional model indicate that the fan meets the specified performance targets, with an expected total-to-static efficiency of 59.4% and a total-to-static pressure rise of 114.7 Pa at the operating point. Experimental tests are performed on the M-fan in order to determine its performance across a full range of flow rates. A range of fan configurations are tested in order to ascertain the effect of tip clearance, blade angle, and hub configuration on fan performance. Due to the lack of a suitable facility for testing a large diameter fan, a scaled 1.542 m diameter model is tested on the ISO 5801 type A fan test facility at Stellenbosch University. A Reynolds-averaged Navier–Stokes CFD model representing the M-fan in the test facility is also developed in order to provide additional insight into the flow field in the vicinity of the fan blades. The results of the CFD model will be validated using the experimental data obtained. Both the CFD results and the experimental data obtained are compared to the initial CFD results for the full scale fan, as obtained in the previous study, by means of fan scaling laws. Experimental data indicate that the M-fan does not meet the pressure requirement set out in the initial study at the design blade setting angle of 34 deg. Under these conditions, the M-fan attains a total-to-static pressure rise of 102.5 Pa and a total-to-static efficiency of 56.4%, running with a tip gap of 2 mm. Increasing the blade angle is shown to be a potential remedy, improving the total-to-static pressure rise and efficiency obtained at the operating point. The M-fan is also shown to be highly sensitive to increasing tip gap, with larger tip gaps substantially reducing fan performance. The losses due to tip gap are also shown to be overestimated by the CFD simulations. Both experimental and numerically obtained results indicate lower fan total-to-static efficiencies than obtained in the initial CFD study. Results indicate that the M-fan is suited to its intended application, however, it should be operated with a smaller tip gap than initially recommended and a larger blade setting angle. Hub configuration is also shown to have an influence on fan performance, potentially improving performance at low flow rates.

Note: A simple laser shutter with protective shielding for beam powers up to 1 W.

We present the design of an inexpensive and reliable mechanical laser shutter and its electronic driver. A camera diaphragm shutter unit with several sets of blades is utilized to provide fast blocking of laser light and protective shielding of the shutter mechanism up to a laser beam power of 1 W. The driver unit is based on an Arduino microcontroller with a motor-shield. Our objective was to strongly reduce construction effort and expenditure by limiting ourselves to a small number of modular parts, which are readily available. We measured opening and closing durations of less than 800 μs, and a timing jitter of less than 25 μs for the fastest set of blades. No degradation of the shutter performance was observed over 5·104 cycles.

Design of Next Generation Civil and Military Aircraft with Ultra-High Bypass Engine using Composites, Advanced Materials and Technology

Indirect combustion noise had not been attracting research in the past, but recent indication seems to prove that it could be a threat in the future if not addressed. Means of reducing this type of noise to a low decibel value was also included. Noise is due to the ingestion of distorted atmospheric turbulence, as the two set of blades rotate in different direction. Open rotor noise is higher since the rotors are fully exposed to oncoming turbulence and lack ducting or a nacelle to attenuate the radiated sound. A thorough review on the technology that can replace conventional turbofan was carried out. It was found that none of this technology can meet up with the ACARE and NASA 2020 vision but left a gap to be filled. Because open rotor is the most proven engine that is able to satisfy this requirements, different methods are adopted and integrated to reduce open rotor noise. Attention was paid to the geometry of the blade, hub and blade length, the vorticity and interaction noise are simulated until an optimized blade was achieved. The integration problem of open rotor was addressed where the engine was located to minimize perceive noise to the payload.

Criteria for Best Performance of Pre-Optimized Solid Dampers

This paper furthers recent research by these authors. The starting point is the pre-optimization of solid dampers, which ensures that all dampers bound to “misbehave” are excluded since the early design stage. The authors now enlarge the scope of their investigations to explore those damper configurations selected inside the admissible design area. The purpose of the paper is to present a set of criteria apt to select a damper configuration which not only avoids unwanted situations, but in addition guarantees high performance under different design conditions. The analysis starts with the definition of a set of requirements a high performance damper should meet. In detail, the present investigation seeks to answer the following questions: in the low excitation regime, what is the frequency shift and the stiffening effect each damper can provide? for increasing excitation levels, which damper will start slipping sooner? in the high excitation regime, which damper provides the maximum dissipation? Like pre-optimization, it does not involve nonlinear finite element calculations, and unlike existing optimization procedures, is not linked to a specific set of blades the damper may be coupled to. The numerical prediction of the blade-damper coupled dynamics is here used only for validation purposes. The approach on which this paper rests is fully numerical; however, real contact parameters are taken from extensive experimental investigations made possible by those purposely developed test rigs which are the distinctive mark of the AERMEC Lab of Politecnico di Torino.

Numerical simulation of tubular turbine applied in wave energy extraction

Overtopping wave energy convertor is becoming increasing popular with the advantages of high efficiency and good reliability. As the core of this type of wave energy extraction device, a shaft tubular turbine with the design head of 15m was optimization designed based on the wave condition somewhere in Shangdong province. Navier-Stokes equations and SIMPLEC algorithm were taken for the numerical simulation of the 3D steady turbulent flow field. By taking consideration of the hydraulic performance of various methods, the best blade airfoil, blade setting angle and guide vane axis were determined. The result shows that the tubular turbine after optimization design not only has the best hydraulic performance with the highest efficiency of 85.36% but also meets the requirement for smooth operation under wave condition. The tubular turbine designed for application in wave energy extraction by numerical simulation is able to supply support for the related research of this field.

Mechanism of stall and surge in a centrifugal compressor with a variable vaned diffuser

To expand the stable operating range of compressors, understanding the mechanism of flow instability at low flow rates is necessary. In this paper, the mechanism of stall and surge in a centrifugal compressor with a variable vaned diffuser is experimentally investigated, where the diffuser blade setting angle can be adjusted. Many dynamic pressure transducers are mounted on the casing surface of the compressor. From the design condition to surge, dynamic pressure data is recorded throughout the gradual process. According to the signal developing status, the typical modes of compressor instability are defined in detail, such as stall, mild surge, and deep surge. A relatively high-frequency stall wave originates in the impeller and propagates to the diffuser, and finally stimulates a deep surge in the compressor. The compressor behavior during surge differs at different diffuser vane angles. When the diffuser vane angle is adjusted, both the unstable form and the core factor affecting the overall machine stability change. A specific indicator is proposed to measure the instability of each component in a compressor, which can be used to determine the best region for stability extension technologies, such as a holed casing treatment, in different compressor applications.

Surgical therapy of ischiofemoral impingement by lateralizing intertrochanteric osteotomy

Lateralizing, derotating intertrochanteric varus osteotomy to increase the ischiofemoral space to counter painful impingement of the lesser trochanter and the os ischium with resulting entrapment of quadratus femoris muscle. Symptomatic ischiofemoral impingement (IFI) caused by Coxa valga et antetorta, Coxa valga or Coxa antetorta, or ashort femoral neck. Anatomic configuration suggestive of IFI in asymptomatic patients. Symptomatic IFI caused by another underlying pathology. Valgus deformity of the knee. Measurement of femoral antetorsion. Planning of the osteotomy, lateralization, varus angle for correction, rotation and offset correction, leg length change, and osteosynthesis plate. General or spinal anesthesia in supine or lateral position. Skin incision (15 cm) beginning lateral of the greater trochanter tip, distally along the axis of the femur. Preparation onto the femur by L‑shaped dissection of the vastus lateralis from the bone. AKirschner(K-)wire is then positioned along the anterior femoral neck to designate the femoral neck antetorsion. Atriangle set on the lateral femoral cortexis is used to determine the osteotomy angle. In the thus determined angle, asecond K‑wire is shot centrally along the femoral neck axis just inferior to its cranial cortex. About 5 mm distal to the second wire, the entry for the blade is prepared using adrill. Using the blade setting instrument, the blade is introduced into the femoral neck, then slightly pulled back. The rotation is then marked on the anterior femoral cortex proximal and distal to the planned osteotomy and the osteotomy is performed. Ablade plate without displacement is impacted. The osteotomy is then reduced, the distal fragment pulled laterally onto the plate, and the screws inserted after compression of the osteotomy with atension device. Touch-toe bearing for 6weeks, then radiological assessment of osteotomy healing before an increase in weight bearing (15 kg/week). Hip flexion limited to90° for 6weeks. Elective implant removal after 12-18months. Studies of this lateralizing varus osteotomy have not been published. The 25-year results of the conventional derotating intertrochanteric varus osteotomy technique show good functional results and low complication rates, with non-union being the most common. Arthroscopic resection of the lesser trochanter has been reported as asurgical alternative in the treatment of IFI in case reports and small series. Advantages of the osteotomy are the restoration of biomechanics and preservation of iliopsoas tendon insertion.

THE EFFECT OF DIFFERENT OPTIONS OF BLADES MAIN ROTOR ON THE X-SHAPED TAIL ROTOR OF THE MI-171 LL

This paper describes the effect of different rotor blades on the X-shaped tail rotor of the Mi-171 LL, observed conducting flight tests. The tests were carried out on the same helicopter in the similar atmospheric conditions. The objective of the tests was the comparison of flight performance of two sets of rotor blades of the helicopter Mi-171 LL. However, materials test revealed a difference in the angles of the tail rotor at different MRs with the same takeoff weight. The authors are grateful to I.G. Peskov, S.R. Zamula and A.I. Orlov for assistance in carrying out this work and the preparation of this article. Noted that the helicopter takeoff weight when hovering out of ground effect in ISA with blades from polymer composite materials (PCM) exceeds the takeoff weight of the helicopter with the serial blades in the nominal mode of the engine operation at ~ 750kg, in the takeoff mode at ~ 700kg. Knowing the altitude and climatic characteristics of the engine, the obtained dependence allows to determine the balancing value of j рв on hovering at different combinations of pressure altitude and outside air temperature for a given speed of the main rotor (MR). It follows from the work that when the same value N пр (95/n нвпр ) 3 or Nfact the balancing values of j рв for the helicopter with the main rotor blades from the PCM is less than for the helicopters with serial blades by 0.5…0.9 ° . The difference in the angles of the tail rotor increases with growing of N епр (95/n нвпр ) 3 (N fact ). Perhaps this is caused by different induction effect of the main rotor on the tail rotor to the MR from PCM and the serial ones. As follows from the materials, the thrust of the main rotor with blades from PCM with the same engine power is more in comparison with the serial blades. Consequently inductive speeds of the main rotor are more and the angles of the tail rotor are less. It can be assumed that a large induced velocity of the main rotor increases the thrust of X-shaped tail rotor.

Best practices for underplatform damper designers

The purpose of this paper is to offer a practical demonstration of how essential preoptimization is in the design of underplatform dampers for turbine blades. Preoptimization can be thought of as a “prescreening” which allows excluding, since the early design stages, a high number of poorly performing damper–platform configurations. This concept, previously presented by the authors, is here extended and its generality for all blade bending modes is rigorously demonstrated. The paper addresses a test case where the introduction of curved-flat underplatform dampers is necessary to avoid a dangerous resonance crossing in the operating rotational speed range of a real turbine disk. It is shown how preoptimized dampers are the only ones that manage to satisfy all functional requirements, including those in the nonlinear operating regime. The same set of dampers may have been identified by exploring, through hundreds of computationally intensive nonlinear calculations, the performance of all possible damper configurations. The latter approach, i.e. iterative design, is unpractical and has to be repeated for each new set of blades since it is based on a test case-specific trial-and-error procedure. Preoptimization substitutes iterations with knowledge of the damper behavior and can therefore be considered as “informed design”: viable damper configurations are instantly singled out through simple but insightful considerations on the damper equilibrium of forces and moments.

Comparison of sensitivities to geometrical properties of front and aft high pressure compressor stages

In modern aviation, the engine-related proportion of the direct operating costs (DOC) is about one quarter. Thereby, the engine-related costs are devided into three roughly equivalent parts: depreciation/financing, fuel and maintenance and overhaul (Rupp in DLRK 2001, 2001). Consequently, an efficient and high technical quality maintenance has a great impact on the DOC. Nowadays, the transition from the exhaust gas temperature based to the condition based maintenance is developing. Thereby, the maintenance, repair and overhaul (MRO) companies provide tailored maintenance actions for each jet engine, depending on the engine history and operation conditions. Obviously, a detailed knowledge of the influence of the different engine components and their features on the engine performance is necessary to accomplish a condition based maintenance. In order to illustrate this, the example of the high pressure compressor (HPC) is shown: The HPC has a strong impact on the gas turbine efficiency and the specific fuel consumption (SFC). Nevertheless, the HPC blading is classified coarsely into serviceable, scrap and repairable. The repairable blades are repaired by a few repair processes, without evaluating the blade geometry in detail. With a detailed knowledge of the geometric main parameters to the aerodynamic performance and their interactions, future repair processes could maintain suited maintenance actions as well as tailored blade sets for the HPC. Therefore, a more efficient maintenance could be achieved to meet future requirements of the costumers. This paper contributes a part to this maintenance development. Therefore, a design of experiments and a sensitivity analysis will be carried out for a HPC-aft stage and compared with previous gained results of a HPC-front stage. Therefore, 700 different stage geometries will be analyzed for their aerodynamic performance and imported to a Kriging Method to generate a meta-model. This meta-model allows a sensitivity analysis for individual geometric properties. The detected sensitivities will be compared to those of the front stage. Changes of the behavior of the stages through the HPC could help the MRO companies to focus on appropriate geometric properties and, therefore, suitable repair processes for each stage and airfoil.

Automated selection and assembly of sets of blades for jet engine compressors and turbines

Aircraft engines need to pass regular maintenance intervals, which go along with a complete disassembly, part inspection (with necessary repair or replacement) and finally reassembly. Especially the manual composition and assembly of blades are time-consuming processes. Increasing air traffic and growing pressure on costs in aviation MRO, demand more efficient approaches. This paper introduces an automated approach for increasing efficiency in selection and assembly of sets of blades for jet engines. Chapter 1 gives a short overview on different designs for compressor and turbine stages. Additionally, the process of adjusting and mounting a set of blades into a circumferential groove is described. Furthermore, a potential for an automated assembly process is determined. Chapter 2 gives an overview of the overall concept, including robotic blade handling, measuring of blades, balancing a set of blades and gap measurement. Chapter 3 focusses on the two measuring tasks. For measuring the width of the blades, optical and tactile approaches are compared. Image processing and laser triangulation are compared to current use of feeler gauges for the gap measurement. In chapter 4 a force-guided assembly strategy, using a force-torque-sensor is presented. Chapter 5 concludes with a brief overview of the planned future work.

A Counter-Rotating Impulse Turbine for Wave Energy Conversion

Wave energy can be converted to the electrical energy by using a wave energy converter. The wave energy converter with oscillating water column (OWC) is one of the most promising devices because of its simple structure and easy maintenance. In this device, an oscillating water column due to the wave motion is used to drive an air column. An air turbine is used to convert the pneumatic energy of this bi-directional airflow into the mechanical energy. The counter-rotating impulse turbine for wave energy conversion has been proposed and tested so far, and the average efficiency has been shown to about 0.3. On the contrary, in another offshore experiment, it has been reported that the power generation efficiency of this turbine is larger than Wells turbine in case of small waves. However, there is a scarcity of the detailed characteristics data of counter-rotating impulse turbine. In a previous study, the authors investigated the effect of rotor blade solidity and setting angle of guide vane on the performance of this turbine, and they clarified that the efficiency of this turbine is higher than impulse turbine with single rotor in the range of high flow coefficients. The present study aimed to investigate the effect of rotor blade profile on the turbine performance by using the computation fluid dynamic (CFD) analysis. The inner and outer angles of turbine rotor blade are changed in the range of 50° to 70°. The commercial CFD software of SCRYU/Tetra of Cradle Co. Ltd. was used in the present work. The Reynolds averaged Navier-Stokes (RANS) equations were used as the governing equations and the low Reynold’s number SST k-ω model was used to predict the turbulent stresses. As a result, it was found that the inner angle of γ = 70° and the outer angle of γ = 60° of the turbine rotor blades can give the best turbine efficiency and it shows the efficiency close to the impulse turbine with single rotor, even in the range of low flow coefficients.

Compressors for Hyper-Sonic Engines —A Theoretical Study of Future Compressors for Hyper Sonic Engines

This paper is an eye opening to the new horizon of the design of operational Compressors in our jet engines. That are compressors usually perform an operation called isentropic process and which levitate the pressure and temperature to the optimum level which require for effective ignition. Basically, our compressors have several sets of blades to perform this function, more precisely saying Rotor and stator blades. Where rotor blade provides air molecule to push at very high velocity to the Stationary blade and when the air Enders to the Stator, the stator races its pressure to move on to the next stage. And we call this set of Stator and rotor as a stage ref [1]. However, in this work, I consider the geometry of the incoming air molecule and how it transforms its physical quantities such as Pressure and temperature ref [2]. For that I tie the concept of Thermodynamic and mechanics on the platform of Tensor analysis ref [3]. That is, I consider the quantities like Pressure, Temperature and rate of flow are their corresponding vector spaces and energy related quintets like heat, work as the scaling elements on the above vector space. And quantities such as entropy enthalpy and specific heat capacity are corresponding physics of it. Considering the advantages, one of the important advantages of this approach is the applicability of results of this work to the formulation of blade less compression Example: Ram and Scram jet engine. Again, the relevant upgrading which is essential for future hypersonic air crafts can achieve from this study and this will be a mile stone for bright air and space travel. To conclude, this approach will be a great transformation on the conventional idea for realization of compression for operational Scram and Ram jet engines ref [4] [5].

Design and Testing of a Cooling Fan for Electro-Mechanical Actuators for Aerospace Applications

Air cooling with wing bay air circulated by axial flow fans is the most suitable and viable way in cooling aircraft Electro-mechanical Actuators (EMAs) used for flight control surfaces. The main objective of the cooling fan is to deliver high static pressure head and high volumetric flow rate overall operating ambient conditions (ambient pressure from 0.2 to 1 atm). In this paper, a preliminary axial flow fan design is first established with the size restriction to fit in the wing bay (diameter of fan is 86 mm). This design is then optimized by conducting a parametric CFD simulation to study the effect of changing the fan blade cord length and blade setting angle. The optimized design is 3D printed and mounted on the motor of a commercially available fan made by Sunon. Both the designed and Sunon fans are tested in a fan loop that has been designed and constructed following the ISO standards. The volume flow rate and the static pressure head are measured at different ambient pressures

Rotor Balancing with Turbine Blade Assembly Using Ant Colony Optimization for Aero-Engine Applications

Abstract The purpose of this paper is to present a novel turbine balancing using Ant Colony Optimization method. Results are compared against well known optimization methods available at open literature. With the new approach, turbine blade set can be separated in to two blade sets as heavy and light blades. This approach makes possible the application of Ant Colony Optimization methodology. ACO methodology is compared with Steepest Descent and Exchange Heuristic methods using nine different initial blade placements. And results are presented. Performance of the three evaluated methods is affected by the initial blade placement. Exchange Heuristics method was quick and provided good results in most of the cases. Ant colony optimization was able find better results than the Steepest Descent method. The approach of separating blades into two sets decreased the solution time of Steepest Descent algorithm. Ant colony optimization method can be used for turbine blade assembly and balancing for aircraft gas turbine applications. This approach is used for the first time in this area and not seen at the open literature.