Investigation of the Effects of Inlet Swirl on Compressor Performance and Operability Using a Modified Parallel Compressor Model PDF Download
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Author: Nicholas Joseph Fredrick
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Book Description
Serpentine ducts used by both military and commercial aircraft can generate significant flow angularity (inlet swirl) and total pressure distortion at the engine face. The impact of inlet swirl on the engine performance and operability must be quantified to ensure safe operation of the aircraft and propulsion system and to define installed deficiencies. Testing is performed over a wide range of flight conditions in the propulsion system flight envelope in order to quantify these effects. Turbine engine compressor models are based on experimental data which can be collected at a limited number of discrete operating points. These models can be used as an analysis tool to optimize the engine test plan and help during validation of the design. The Dynamic Turbine Engine Compressor Code (DYNTECC) utilizes parallel compressor theory and quasi-one-dimensional Euler equations to determine compressor performance. In its standard form, DYNTECC uses user-supplied characteristic stage maps in order to calculate stage forces and shaft work for use in the momentum and energy equations. These maps are typically developed using experimental data. These maps can also be created using characteristic codes such as the 1-D Mean Line Code (MLC) or the 2-D Streamline Curvature Code. The MLC was originally created to predict the performance of individual compressor stages and requires greatly reduced computational time when compared to 2-D and 3-D models. This thesis documents work done to incorporate the MLC into DYNTECC as a subroutine. The combine DYNTECC/MLC was then used to analyze the effects of inlet swirl on the fan performance and operability of the Honeywell F109 turbofan engine. The code was calibrated and validated using the F109 cycle deck. Additional code validation was performed using experimental data gathered at the United States Air Force Academy (USAFA). F109 fan maps were developed for various cases of inlet swirl and results were presented showing shifts in corrected mass flow, fan pressure ratio and fan stability limit.
Author: Nicholas Joseph Fredrick
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Book Description
Serpentine ducts used by both military and commercial aircraft can generate significant flow angularity (inlet swirl) and total pressure distortion at the engine face. The impact of inlet swirl on the engine performance and operability must be quantified to ensure safe operation of the aircraft and propulsion system and to define installed deficiencies. Testing is performed over a wide range of flight conditions in the propulsion system flight envelope in order to quantify these effects. Turbine engine compressor models are based on experimental data which can be collected at a limited number of discrete operating points. These models can be used as an analysis tool to optimize the engine test plan and help during validation of the design. The Dynamic Turbine Engine Compressor Code (DYNTECC) utilizes parallel compressor theory and quasi-one-dimensional Euler equations to determine compressor performance. In its standard form, DYNTECC uses user-supplied characteristic stage maps in order to calculate stage forces and shaft work for use in the momentum and energy equations. These maps are typically developed using experimental data. These maps can also be created using characteristic codes such as the 1-D Mean Line Code (MLC) or the 2-D Streamline Curvature Code. The MLC was originally created to predict the performance of individual compressor stages and requires greatly reduced computational time when compared to 2-D and 3-D models. This thesis documents work done to incorporate the MLC into DYNTECC as a subroutine. The combine DYNTECC/MLC was then used to analyze the effects of inlet swirl on the fan performance and operability of the Honeywell F109 turbofan engine. The code was calibrated and validated using the F109 cycle deck. Additional code validation was performed using experimental data gathered at the United States Air Force Academy (USAFA). F109 fan maps were developed for various cases of inlet swirl and results were presented showing shifts in corrected mass flow, fan pressure ratio and fan stability limit.
Author: Reggie Floyd
Publisher:
ISBN:
Category :
Languages : en
Pages : 88
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Book Description
Engine inlet distortion complications have plagued the turbine engine development community for decades, and engineers have developed countless methods to identify and combat the harmful effects of inlet distortion. One such type of distortion that has gained much attention in recent years is known as inlet swirl, which results in a significant flow angularity at the face of the engine. This flow angularity can affect the pressure rise and flow capacity of the fan or compressor, and subsequently affect compressor and engine performance. Previous modeling and simulation efforts to predict the effect inlet swirl can have on fan and compressor performance have made great strides, yet still leave a lot to be desired. In particular, a one-dimensional parallel compressor model called DYNTECC (Dynamic Turbine Engine Compressor Code) has been used to analyze the effects of inlet swirl on fan and performance operability of the Honeywell F109 turbofan engine. However, when compared to experimental swirl data gathered at the United States Air Force Academy (USAFA), the model predictions were found to be inaccurate. This thesis documents work done to compare the initial predictions generated by DYNTECC to the latest set of experimental swirl data, analyze the potential shortcomings of the initial model, and modify the existing model to more accurately reflect test data. Extensive work was completed to create a methodology that can calibrate the model to existing clean inlet fan map data. In addition, an in depth study of fan/compressor stalling criteria was conducted, and the model was modified to use an alternate stalling criteria that more accurately predicted the point of stall for various swirl inlet conditions. The prediction of the fan stall pressure ratio for all inlet swirl conditions tested is within 2% of the ground test stall point at the same referred fan speed and referred mass flow.
Author: Joshua Scott Coughenour
Publisher:
ISBN:
Category :
Languages : en
Pages : 66
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Book Description
Engine inlet distortion, more specifically inlet swirl, has created much angst and proved just how little of a true understanding engineers today have of the true effect inlet swirl has on engine performance. Engineers have attempted to developed procedures and computer codes to detect, predict, and mitigate the performance degrading effects of inlet distortion. Inlet distortion has been the hot topic in recent years due to the large amount of flow angularity inlet swirl can produce at the face of the engine compressor. While inlet distortion work over the past years has proved to be beneficial to the engine development community there are still variables and engine performance degradation attributes needing further exploration. Pressure distortion accompanied with inlet swirl has proved to be an area of interest. Since inlet swirl results in flow angularity at the engine face, potentially resulting in a pressure rise, being able to predict swirl with pressure distortion together can provide a better understanding of just how much overall distortion could be present at the engine face, subsequently affect compressor and engine performance. Previous modeling and simulation (M&S) efforts to predict the effect inlet swirl can have on fan and compressor performance have come a long way, yet still leave many unknowns. This study, of a one-dimensional parallel compressor model called DYNTECC (Dynamic Turbine Engine Compressor Code), was used to analyze the effects of inlet swirl and pressure distortion on fan and performance operability of the Honeywell F109 turbofan engine. This thesis documents the work done to compare the DYNTECC predictions, that included both swirl and pressure distortion, to DYNTECC data sets that were solely based on swirl distortion to further understand the effects single and combined distortion sources have on the F109 engine. It can be concluded that, while pressure distortion present at the fan face of a F109 engine does degrade engine performance, there is minimal impact when pressure distortion is the only source of inlet distortion present. The 1.6% difference from the 15% pressure distortion, no swirl case is the largest difference for all conditions tested in this thesis, except for the 150 twin-swirl with 15% pressure distortion case which has an 1.8% difference. This confirms, in most cases in which pressure distortion is paired with swirl distortion in the F109 engine, the swirl distortion is the main contributor to engine performance degradation.
Author: Huafeng Ding
Publisher: Springer Nature
ISBN: 9811666407
Category : Technology & Engineering
Languages : en
Pages : 187
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Book Description
This book collects chapters on Aerospace Mechatronics and Control Technology as selected contributions from the 7th Asia Conference on Mechanical Engineering and Aerospace Engineering (MEAE) in 2021. The book focuses on novel techniques for aviation infrastructure in aerospace mechatronics and avionics systems, mechanical engineering in aerospace, and mechanical design and control system domains. The contents make valuable contributions to academic researchers and engineers in the industry. The MEAE 2021 provides a forum to discuss the latest trends and advances in mechanical engineering and aerospace engineering and related fields, and foster the exchange of ideas and international collaboration in the field.
Author: Wolfram Pazur
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 0
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Book Description
Aeroengine intakes containing S-shaped diffusers produce different types of inlet swirl distortions and essentially a combination of a twin swirl and a bulk swirl. The main object of this investigation was to assess the influence of inlet swirl distortions on the performance of a transonic two-stage axial compressor installed in a turbo jet bypass engine Larzac 04. A typical inlet swirl distortion was simulated by a delta-wing in front of the engine. An experimental method was investigated to measure the performance map of the installed low-pressure compressor for different engine operating lines. The influence of an inlet swirl distortion with different strengths on the performance map of the compressor was investigated experimentally. It is shown that the performance parameters decrease and a temperature distortion is generated behind the compressor. As the basis of the theoretical investigations of the performance map, including inlet swirl distortions, a computing model considering four compressors working in parallel was established. The model is based on the idea that an inlet swirl distortion can be substituted by two fundamental types of swirl components, i.e., a bulk swirl corotating, and a bulk swirl counterrotating to the revolution of the compressor. Computed performance maps of the compressor will be discussed and compared with the experimental data.
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781719974660
Category : Science
Languages : en
Pages : 26
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Book Description
An investigation of surge was conducted by using a parallel compressor model of the J85-13 compressor implement on an analog computer. Surges were initiated by various types of dynamic disturbances in inlet pressure. The compressor model was less sensitive to disturbances of short duration, high frequency, and long duration where the compressor discharge pressure could react. Adding steady distortion to dynamic disturbances reduced the amount of dynamic disturbance required to effect surge. Steady and unsteady distortions combined linearly to reduce surge margin. Wenzel, L. M. and Blaha, R. J. Glenn Research Center NASA-TM-X-3522, E-8979 RTOP 505-05
Author: Karl Kovach
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
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Book Description
Author: Eddie Y.K. Ng
Publisher: Springer Science & Business Media
ISBN: 3540724125
Category : Technology & Engineering
Languages : en
Pages : 154
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Book Description
This book brings together the quick integral approaches and advances in the field for the prediction of stall and surge problems in the compressor. The book is useful for people involved in the flow analysis, design and testing of rotating machinery. For students, it can be used as a specialized topic of senior undergraduate or graduate study. The book can also serve as self-study material.
Author: Leon M. Wenzel
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 22
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Book Description
An investigation of surge was conducted by using a parallel compressor model of the J85-13 compressor implement on an analog computer. Surges were initiated by various types of dynamic disturbances in inlet pressure. The compressor model was less sensitive to disturbances of short duration, high frequency, and long duration where the compressor discharge pressure could react. Adding steady distortion to dynamic disturbances reduced the amount of dynamic disturbance required to effect surge. Steady and unsteady distortions combined linearly to reduce surge margin.
Author: J. Cary Nettles
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
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Book Description
For a Mach number range from 1.6 to 2.0 and angles of attack from 0 to 9 degrees the occurrence of stall was related to the presence of a pressure deficiency at the hub of the compressor. The referred engine air flow tended to increase as radial distortion level increased. Approaching the inlet buzz limit with the engine operating in or near a stall condition did not affect the minimum stable air flow of the diffuser, and conversely the presence of mild buzz did not affect the compressor stall limit. The stability limits of a 15 degree plus 10 degree double-cone inlet were essentially the same with the engine as with a choked plug.
