The dynamic response of the compression system is a key factor in determining the operability characteristics of an aircraft gas turbine engine subjected to various transient environmental and control inputs. Computer models have been developed to simulate this response. The primary inputs to these models are the wide-range, steady-state compressor stage characteristics. To reduce the dependence of these dynamic models on experimental performance data, significant effort has been devoted to the development of stage characteristic prediction techniques. As part of this ongoing effort, a model to simulate rotating stall inception and development in axial-flow compressor stages was constructed. This model was applied to an isolated rotor build to investigate the sensitivity of the predicted stall behavior to the shape of the high-incidence portions of the blading relative total pressure loss and turning angle characteristics, as well as to the rotor speed. In addition, the predicted steady-state, stalled rotor performance was compared with corresponding low-speed, experimental data. By superimposing small flow perturbations on the rotor flow field over a range of initial operating conditions, it was demonstrated that stall inception occurs only for initial relative flow incidence near some critical value, defined as the incidence for which the relative total pressure losses incurred in the blade passage increase sharply. For initial operating points away from the critical one, no propagating disturbance was predicted. Also, a strong sensitivity of the predicted stall behavior to the shape of the high-incidence portion of the relative total pressure loss characteristic was observed with increased-slope curves resulting in earlier stall inception and larger amplitude stall disturbances. The effect of increased-slope loss curves on the predicted steady-state rotor performance was to cause a more abrupt drop in the flow and total pressure rise coefficients at the stall limit. Comparatively, varying the shape of the turning angle characteristic or the rotor speed had only a slight effect on the simulated rotating stall phenomena. Finally, the predicted install total pressure characteristic for a selected low-speed case was compared with experimental data with favorable results. / Master of Science

This thesis discusses the experimental modal analysis work done on a reciprocating Freon compressor. The primary goal of this work was to aid in the development of a dynamic finite element model for the compressor. The crankcase, the compressor shell, and the entire compressor were each studied individually so that the characteristics of each component could be determined separately. For each of the tested elements, a modal survey was done followed by the determination, with the use of a laser, of the forced frequency response shapes associated with each resonance. These shapes, along with the associated frequencies, were compared with the results from the finite element analysis model to determine if the model needed to be updated. The crankcase was also tested to determine if a rigid-body assumption would be valid for the purpose of force analysis. This study resulted in the experimental data that could be used for comparison with the finite element model results. In general, the forced frequency response shapes could be matched to the finite element mode shapes up to 1400 Hz for the empty shell and assembled compressor, 2000 for the crankcase. Also, there were several conclusions that resulted from this study. These included acceptance of the rigid-body assumption for purposes of the force analysis, the need for a further look at the dynamic variations between individual compressors, and a suggestion to move the suspension mounts to the narrow side from the broad side. / Master of Science

The oil-film surface flow visualization technique was applied to circular arc compressor blades in a solid wall, high aspect ratio cascade for the purpose of describing the transition from corner stall to full blade stall, and the blade surface flow under fully stalled conditions. Photos of the visualizations for three stagger angles are presented and analyzed. A map quantitatively describing the observed boundary layer development at midspan is presented. The most interesting discovery of the work showed the suction surface flow to be essentially two-dimensional, in the geometric sense, preceding and following the transition to a fully separated flow at the leading edge. Corner stall was the observed three-dimensional mechanism prior to full stall. For fully-stalled conditions, the three-dimensional mechanism took the form of recirculating flow regions at the blade ends. Complete separation at the leading edge occurred at lower angles of attack for the higher stagger angles. Special blade oil-flow tests were conducted to evaluate Reynolds number and tip clearance effects on boundary layer development. The experimental work was done as part of a larger research program aimed at measuring and predicting the stalled performance of a compressor cascade. / Master of Science

Orientador: Jose Roberto de França Arruda / Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecanica / Made available in DSpace on 2018-08-05T19:37:58Z (GMT). No. of bitstreams: 1 Nunes_Osmar_M.pdf: 3751336 bytes, checksum: 2fc3b9c3cc2af03451617cae482065d1 (MD5) Previous issue date: 2005 / Resumo: As características acústicas de compressores herméticos têm se tomado cada vez mais críticas no projeto destes equipamentos e as predições destas características ao longo do projeto, obrigatórias para a adequação deste produto às condições de consumo. Este trabalho apresenta um método de avaliação vibro-acústica de compressores herméticos através de modelos de elementos finitos. Para estas avaliações, forças harmônicas com amplitudes unitárias são aplicadas em pontos específicos da carcaça e os seus campos de pressão sonora resultantes são calculados sob condições anecóicas, sendo que, estas condições foram modeladas através de elementos infinitos acústicos. Através deste método, é possível obter numericamente a potência acústica irradiada por diferentes versões de projeto, compará-las, escolher a versão mais adequada e, se for o caso, obter informações para direcionar modificações em uma versão para a sua adequação aos níveis de potência sonora exigidos. O trabalho mostra as verificações executadas durante o processo de desenvolvimento desta metodologia como análise modal, análises de convergência e comparações de resultados numéricos com analíticos através de modelos de fontes omnidirecionais. Para a verificação de seu funcionamento, são apresentadas as análises vibro-acústicas numéricas de duas versões de compressor. Além disto, dois protótipos com características semelhantes aos modelos analisados foram testados em câmara reverberante para a obtenção de suas potências sonoras e a comparação com os resultados numéricos. Os resultados obtidos desta comparação mostraram boas correlações entre numérico e experimental e fornecem subsídios para avaliar o desempenho entre as diferentes versões de projeto / Abstract: The importance of the acoustic characteristics in design of hermetic compressors has increased along the years. As a consequence, to predict these characteristics in the design phase is mandatory for this product to meet the consumption requirements. This work presents a method for evaluating the vibration and acoustic characteristics of hermetic compressors through finite element models. To perform these evaluations, harmonic forces with unitary amplitudes are applied in specific locations of the compressor housing and their resulting acoustic pressure fields are ca1culated under anechoic conditions obtained through the acoustic infinite elements. By using this method, it is possible to numerically obtain the acoustic power level irradiated by different versions of design in order to compare them and to choose the most adequate version. With the use of this method it is also possible to obtain information to guide modifications in the design and suit it to desired acoustic power levels. This work presents the verifications performed during the development process of this methodology such as modal analysis, convergence analysis and comparisons between analytical and numerical results by using omnidirectional sources. To validate this methodology, the acoustic numerical analysis of two versions of compressor' s housing was presented. Furthermore, two prototypes similar to the models characteristics were submitted to tests in reverberant chamber for obtaining their acoustic power levels and compared with the numerical results. The obtained results of this comparison presented a satisfactory correlation between numerical and experimental results and provided relevant information to evaluate different design versions / Mestrado / Mecanica Computacional / Mestre em Engenharia Mecânica

Thesis (MScEng)--Stellenbosch University, 2006. / ENGLISH ABSTRACT: The Stellenbosch University Compressor Code (SUCC) has been developed for the purpose of predicting the performance of axial flow compressors by means of axisymmetric inviscid throughflow methods with boundary layer blockage and empirical blade row loss models. This thesis describes the process of the implementation and verification of a number of stall prediction criteria in the SUCC. In addition, it was considered desirable to determine how certain factors influence the accuracy of the stall prediction criteria, namely the nature of the computational grid, the choice of throughflow method used, and the use of a boundary layer blockage model and a radial mixing model. The stall prediction criteria implemented were the di®usion factor limit criterion, de Haller's criterion, Aungier's blade row criterion, Aungier's boundary layer separation criterion, Dunham's, Aungier's and the static-to-static stability criteria. The compressors used as test cases were the Rofanco 3-stage low speed compressor, the NACA 10-stage subsonic compressor, and the NACA 5-stage and 8-stage transonic compressors. Accurate boundary layer blockage modelling was found to be of great importance in the prediction of the onset of stall, and that the matrix throughflow Method provided slightly better accuracy than the streamline curvature method as implemented in the SUCC by the author. The ideal computational grid was found to have many streamlines and a small number of quasi-orthogonals which do not occur inside blade rows. Radial mixing modelling improved the stability of both the matrix throughflow and streamline curvature methods without significantly affecting the accuracy of the stall prediction criteria. De Haller's criterion was over-conservative in estimating the stall line for transonic conditions, but more useful in subsonic conditions. Aungier's blade row criterion provided accurate results on all but the Rofanco compressor. The diffusion factor criterion provided over- optimistic predictions on all machines, but was less inaccurate than de Haller's criterion on the NACA 5-stage transsonic machine near design conditions. The stability methods performed uniformly and equally badly, supporting the claims of other researchers that they are of limited usefulness with throughflow simulations. Aungier's boundary layer separation method failed to predict stall entirely, although this could reflect a shortcoming of the boundary layer blockage model. / AFRIKAANSE OPSOMMING: Die Stellenbosch University Compressor Code (SUCC) is ontwikkel om die prestasie van aksiaalvloei kompressors te voorspel met behulp van aksisimmetriese nie-viskeuse deurvloeimetodes met grenslaagblokkasie en empiriese modelle vir die verliese binne lemrye. Hierdie tesis beskryf die proses waarmee sekere staakvoorspellingsmetodes in die SUCC geïmplementeer en geverifieer is. Dit was ook nodig om die effek van sekere faktore, naamlik die vorm van die berekeningsrooster, die keuse van deurvloeimetode en die gebruik van `n grenslaagblokkasiemodel en radiale vloeivermengingsmodel op die akuraatheid van die staakvoorspellingsmetodes te bepaal. Die staakvoorspellingsmetodes wat geïmplementeer is, is die diffusie faktor beperking metode, de Haller se metode, Aungier se lemrymetode, Aungier se grenslaagmetode en die Dunham, Aungier en die statiese-tot-statiese stabiliteitsmetodes. Die kompressors wat gebruik is om die metodes te toets is die Rofanco 3-stadium lae-spoed kompressor, die NACA 10-stadium subsoniese kompressor en die NACA 5- en 8-stadium transsoniese kompressors. Daar is vasgestel dat akkurate grenslaagblokkasie modelle van groot belang was om `n akkurate aanduiding van die begin van staking te voorspel, en dat, vir die SUCC, die Matriks Deurvloei Metode oor die algemeen 'n bietjie meer akkuraat as die Stroomlyn Kromming Metode is. Daar is ook vasgestel dat die beste berekeningsrooster een is wat baie stroomlyne, en die kleinste moontlike getal quasi-ortogonale het, wat nie binne lemrye geplaas mag word nie. Die numeriese stabiliteit van beide die Matriks Deurvloei en die Stroomlyn Kromming Metode verbeter deur gebruik te maak van radiale vloeivermengingsmodelle, sonder om die akkuraatheid van voorspellings te benadeel. De Haller se metode was oorkonserwatief waar dit gebruik is om die staak-lyn vir transsoniese vloei toestande, maar meer nuttig in die subsoniese vloei gebied. Aungier se lemrymetode het akkurate resultate gelewer vir alle kompressors getoets, behalwe die Rofanco. Die diffusie faktor metode was oor die algemeen minder akuraat as Aungier se metode, maar meer akkuraat as de Haller se metode vir transsoniese toestande. Die stabiliteitsmetodes het almal ewe swak gevaar. Dit stem ooreen met die bevindings van vorige navorsing, wat bewys het dat hierdie metodes nie toepaslik is vir simulasies wat deurvloeimetodes gebruik nie. Aungier se grenslaagmetode het ook baie swak gevaar. Waarskynlik is dit as gevolg van tekortkomings in die grenslaagblokkasiemodel.

Approved for public release, distribution is unlimited / The flow around second-generation controlled-diffusion blades in cascade at stall was examined experimentally through the use of a two-component laser-Doppler velocimeter. Blade surface pressure measurements were also preformed at mid span on the blades at various Reynolds numbers. Flow visualization techniques were used to observe and record the flow on the surface of the blade. A correlation between the experimental results and computational fluid dynamic predictions was attempted in order to determine the exact nature of the flow as the blades approached stall, to further assist in the development of advanced blade design. The blade surface pressure measurements showed that the mid-span section of the blade was at a lower loading than previously measured at a smaller inlet flow angle. This indicated that the blade section was at stall. The flow visualization highlighted the extent of the three-dimensional flow over the blades. The LDV measurements documented the mid-span boundary layer and wake profiles. / Ensign, United States Navy

För att skapa konkurrenskraft krävs alltid optimering, av flera olika processer, mot mer energi- och kostnads-effektivitet. Anläggningen som används i detta projekt, ett kraftvärmeverk som byggdes så sent som 2015, har dragits med vad som verkat vara en icke optimal drift av tryckluftssystemet med tre identiska, frekvensomformarstyrda kompressorer. Målsättningen med detta projekt var att ta fram förslag på en mer optimal styrning av anläggningens tre kompressorer samt att implementera den för att genomföra en analys om resultatet. En nulägesanalys visade att det fanns utrymme för förbättring av styrningen samt att en del regulatorparametrar skulle behöva optimeras. Två regleringsförslag togs fram, som till stor del vara ganska lika men med den stora skillnaden att förslag ett använda sig av kompressorernas tryckregulatorer och det andra förslaget styrde kompressorernas varvtal direkt från PLC:n. I slutet på detta projektet, när de nya regleringsförslagen skulle implementeras, var anläggningen i ett tre veckor långt driftstopp för underhåll. Detta påverkade optimeringen genom att förbrukningen av tryckluft var låg. Detta skulle lett till att en parameteroptimering inte skulle blivit helt optimal. Eftersom kompressortillverkaren inte valde att samarbeta fanns dessutom ingen möjlighet att utföra en parameteroptimering på alla regulatorer. Trots dessa omständigheter så har en viss optimering troligen skett med det nya regleringsförslaget. / In order to create competitiveness, optimization towards more energy and cost efficiency is always required, of several different processes. The plant used in this project, a cogeneration plant that was built as late as 2015, has been drawn with what appeared to be a non-optimal operation of the compressed air system with three identical air compressors whom are controlled by frequency converters. The objective of this project was to produce proposals for a more optimal control of the plant's three air compressors and to implement it to carry out an analysis of the result. An analysis of the origin operation showed that there was room for improvement of the control and that some controller parameters would need to be optimized. Two regulatory proposals were developed, which to a large extent are quite similar but with the great difference that the first proposal make use of the compressors' pressure controllers and the other proposal controlled the speed of the compressors directly from the PLC. At the end of this project, when the new regulatory proposals were to be implemented, the facility was in a three-week downtime for maintenance. This affected the optimization because the consumption of compressed air was low. This would mean that a parameter optimization would not be completely optimal. Moreover, since the compressor manufacturer did not choose to cooperate, there was no possibility of performing a parameter optimization on all controllers. Despite these circumstances, some optimization has probably occurred with the new regulatory proposal.

The numerical simulation model presented is based on the integration of the fluid conservation equations (continuity, momentum and energy) in the whole compressor domain (compression chamber, valves, manifolds, mufflers, connecting tubes, parallel paths, etc.) using instantaneous local mean values for the different variables. It is interesting to remark how momentum equation has been taken into account in all compressor parts and the possibility to solve parallel paths, resonators, etc. Effective flow areas are evaluated considering multidimensional models based on modal analysis of fluid interaction in the valve. Then, second and third order vibration models of valve are also considered. The possibility to use compound bound has been also implemented.The force balances in the crankshaft connecting rod mechanical system are simultaneously solved at each time-step considered in the thermal and fluid dynamic compressor model. It allows to evaluate the instantaneous compression chamber volume and the different forces in the crankshaft connecting rod mechanical system. Mechanical system forces allows to know important information to predict possibleover-stresses in piston, piston pin, crankshaft, connecting rod, etc.The thermal analysis of the solid elements is based on global energy balances at each macro volume considered (shell, muffler, tubes, cylinder head, crankcase, motor, etc.). Some improvements can be implemented (shell conduction, heat transfer coefficient evaluation, etc.).The resulting governing equations (fluid flow, valve dynamics, conduction heat transfer in solids, etc.) are discretized by means of a fully implicit control volume formulation. The complete set of algebraic equations are coupled using the segregated he complete set of algebraic equations are coupled using the segregated pressure based algorithm Semi-Implicit Method for Pressure-Linked Equations(SIMPLEC) extended to compressible flow. Second and third time order schemes have been implemented for the transient terms.An extensive hermetic reciprocating compressor experimental validation has been presented and the experimental know-how acquired has been highlighted. Furthermore, two commercial hermetic reciprocating compressor have been instrumented in detail to obtain the thermal temperatures map and the pressure fluid evolutions along compressor for different working conditions. It is interesting to remark as a novelty, the use of very small absolute pressure transducers, instead of the standard relative transducers. They allow to know instantaneous absolute pressure inside compressor chamber, without the necessity of measurement an absolute pressure outside the compression chamber (as is usual in this kind of experimental works). The global comparative results have allowed to check the possibilities of the numerical simulation presented above and its accuracy compared with experimental data. After that, this work show the capabilities offered by the simulation presented and its final objective, a better understanding of the thermal and fluid dynamic compressor behaviour to improve the design of these equipments.Then, the objective has been to review and present different physically meaningful parameters that characterize the reciprocating compressor behaviour (volumetric efficiency, isentropic efficiency, heat transfer efficiency, mechanical, electrical and heat losses, Coefficient of Performance, etc.), their influence detachment and evolution under different working conditions, with the idea to predict the performance of hermetic reciprocating compressors under different working conditions using the above mentioned non-dimensional parameters.Finally, a parametric study of hermetic reciprocating compressors behaviour has been carried out. Results presented show the influence of different aspects (geometry, valves, motor, working conditions, etc.) in the compressor behaviour. The parametric studies and compressor characterization detachment allows also a better implementation of simplest models of the compressors in the thermal and fluid dynamic numerical simulation of vapour compressor cycles together with the rest of elements.

abstract: This thesis presents a new technique to develop an air-conditioner (A/C) compressor single phase induction motor model for use in an electro-magnetic transient program (EMTP) simulation tool. The method developed also has the capability to represent multiple units of the component in a specific three-phase distribution feeder and investigate the phenomenon of fault-induced delayed voltage recovery (FIDVR) and the cause of motor stalling. The system of differential equations representing the single phase induction motor model is developed and formulated. Implicit backward Euler method is applied to numerically integrate the stator currents that are to be drawn from the electric network. The angular position dependency of the rotor shaft is retained in the inductance matrix associated with the model to accurately capture the dynamics of the motor loads. The equivalent circuit of the new model is interfaced with the electric network in the EMTP. The dynamic response of the motor when subjected to faults at different points on voltage waveform has been studied using the EMTP simulator. The mechanism and the impacts of motor stalling need to be explored with multiple units of the detailed model connected to a realistic three-phase distribution system. The model developed can be utilized to assess and improve the product design of compressor motors by air-conditioner manufacturers. Another critical application of the model would be to examine the impacts of asymmetric transmission faults on distribution systems to investigate and develop mitigation measures for the FIDVR problem. / Dissertation/Thesis / M.S. Electrical Engineering 2012

The modern trend of gas turbines design is towards lighter, highly efficient,and more compact engines. Such situation imposes on engineers to continuouslysearch for improved and optimum designs. The thesis presented aims at researching possible performance improvements regarding axial gapdistance in transonic compressors. Decreasing the axial gap would result inlighter engines and achieve design goals. The influence of decreasing the axialgap on performance and structure integrity should be throughly analyzed. This thesis work includes numerical investigations on the axial gap distance effect on performance efficiency and related unsteady aerodynamics phenomena. The first one and a half compressor stages of a Siemens Gas Turbine are modeled in ANSYS CFX. Different axial gap models are simulated for differentconfigurations. The steady state solution is obtained to be initialized for transient time marching calculations. Furthermore, the computational cost of transient calculations is reduced through a geometry scaling technique. The unsteady behavior is further analyzed by a Harmonic Balance solver implemented in STAR-CCM+ software, and compared to a reference case transient calculations. The results obtained supports the presence of an optimalaxial gap distance for maximum efficiency in transonic compressors. Further, the harmonic balance method shows good possibilities for cost and time reductions in transonic compressors performance calculations.