Turbine Engine

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Pawel Wirkowski - One of the best experts on this subject based on the ideXlab platform.

  • influence of the incorrect settings of axial compressor inlet variable stator vanes on gas Turbine Engine work parameters
    Journal of KONES, 2015
    Co-Authors: Pawel Wirkowski
    Abstract:

    The paper deals with the problem of influence of changes variable stator vanes axial compressor settings of gas Turbine Engine on work parameters of compressor and Engine. Incorrect operation of change setting system of variable vanes could make unstable work of compressor and Engine. This paper presents theoretical analysis of situation described above and results of own research done on real Engine. When in the compressor construction there is assembled system of setting change of variable stator vanes its task is to make optimal cooperation Engine units during the permanent improvement of compressor characteristic. Perturbations in the operation of this system could cause changes in work of compressor and Engine similarly as in the case of changes caused by changes of rotational speed or polluted interblades ducts of compressor. The purpose of investigations, which was carried out on real Engine was determination influence of incorrect operation of axial compressor inlet guide variable stator vanes control system of gas Turbine Engine on compressor and Engine work parameters. The object of research is type DR 77 marine gas Turbine Engine, which is a part of power transmission system of war ship. In compressor construction configuration of this Engine there are used inlet guide stator vanes which make possibilities to change the setting angle incidance (change of compressor flow duct geometry) in depend on Engine load. On the base of results of experiment there were determined the mathematical equations modelling the changes of particular Engine work parameters in the function of variable inlet guide stator vanes setting angle.

  • influence of axial compressor flow passage geometry changes on gas Turbine Engine work parameters
    Journal of Polish CIMAC, 2009
    Co-Authors: Pawel Wirkowski
    Abstract:

    The paper deals with the problem of influence of changes variable stator vanes axial compressor settings of gas Turbine Engine on work parameters of compressor and Engine. Incorrect operation of change setting system of variable vanes could make unstable work of compressor and Engine. This paper presents theoretical analysis of situation described above and results of own research done on real Engine. On the base of results of experiment there were determined mathematical equations determining relationships of changes of particular Engine work parameters in function of variable inlet guide stator vanes setting angle. There are presented results of the solution of mathematical equations, which describe the changes of Engine work parameters values too.

  • research of variation of gas Turbine Engine work parameters changes equipped with changeable geometry of axial compressor flow passage
    Journal of Polish CIMAC, 2008
    Co-Authors: Pawel Wirkowski
    Abstract:

    The paper deals with problem influence of changes variable stator vanes axial compressor settings of gas Turbine Engine on work parameters of compressor and Engine. Incorrect operation of change setting system of variable vanes could make unstable work of compressor and Engine. This paper presents theoretical analysis of situation described above and results of own research done on real Engine. The next there are presented results of mathematical modelling of changes of gas Turbine Engine work parameters during change of angle setting of axial compressor variable stator vanes but in the most wide angle range than in real research.

Jinwoo Seok - One of the best experts on this subject based on the ideXlab platform.

  • Coordinated Model Predictive Control of Aircraft Gas Turbine Engine with Simplified Electrical System Model
    2018 Annual American Control Conference (ACC), 2018
    Co-Authors: Jinwoo Seok, Ilya V. Kolmanovsky, David M Reed, Anouck R. Girard
    Abstract:

    With the trends towards More Electric Aircraft and All Electric Aircraft, the electrical power requirements for aircraft have been steadily increasing, making the interactions between the electrical system and gas Turbine Engine significant and requiring advanced control strategies for safe and efficient operation of the aircraft. Thus, in this paper, a coordinated control strategy for a gas Turbine Engine, an advanced dual generator subsystem, and energy storage elements with a simplified electrical bus model, is developed to accommodate large transient thrust and electrical loads. A rate-based Model Predictive Control approach is utilized to track setpoints and ensure system constraints. The bus voltage behaviors are stabilized by imposing a power rate constraint without having additional states in the controller design. Energy storage elements assist the generators to improve system performance as well as the transient bus voltage behavior. The incorporation of energy storage elements provides the potential to extend system operation range for future more electric aircraft and all electric aircraft.

  • coordinated model predictive control of aircraft gas Turbine Engine and power system
    Journal of Guidance Control and Dynamics, 2017
    Co-Authors: Jinwoo Seok, Ilya V. Kolmanovsky, Anouck Girard
    Abstract:

    Motivated by the growing need to accommodate large transient thrust and electrical load requests in future more-electric aircraft, a coordinated control strategy for a gas Turbine Engine, generators, and energy storage is developed. An advanced two-generator configuration, with each generator connected to a shaft of the gas Turbine Engine, is treated. Model predictive control maximizes system performance and protects this system against constraint violations. The controller design is exploits rate-based linear prediction models. In addition, an auxiliary offset state improves the match between the linear prediction model and the nonlinear system. The auxiliary offset state allows the system to be controlled over the large operating range without requiring multiple linearizations/controllers. The advantages of different energy storages are also compared to complement the two-generator configuration in a more electric aircraft. Primary results indicate that the coordinated model predictive control with an a...

  • coordinated model predictive control of aircraft gas Turbine Engine and power system
    Journal of Guidance Control and Dynamics, 2017
    Co-Authors: Jinwoo Seok, Ilya V. Kolmanovsky, Anouck Girard
    Abstract:

    Motivated by the growing need to accommodate large transient thrust and electrical load requests in future more-electric aircraft, a coordinated control strategy for a gas Turbine Engine, generator...

  • integrated coordinated control of aircraft gas Turbine Engine and electrical power system towards large electrical load handling
    Conference on Decision and Control, 2016
    Co-Authors: Jinwoo Seok, Ilya V. Kolmanovsky, Anouck Girard
    Abstract:

    The paper considers a problem of integrated thrust and electrical power management for an aircraft. An advanced configuration of the aircraft electrical power system consisting of two generators driven by the gas Turbine Engine is considered. A Model Predictive Controller is designed to respond to thrust and electrical load commands while maintaining system operation at high efficiency setpoints and satisfying the input and state constraints, including surge margin limits. The design steps are described and closed-loop simulation results are reported based on the nonlinear system model.

S R Gollahalli - One of the best experts on this subject based on the ideXlab platform.

  • performance and emission characteristics of biofuel in a small scale gas Turbine Engine
    Applied Energy, 2010
    Co-Authors: Zehra Habib, R N Parthasarathy, S R Gollahalli
    Abstract:

    Performance and emissions characteristics of a 30Â kW gas Turbine Engine burning Jet A, soy methyl ester, canola methyl ester, recycled rapeseed methyl ester, hog-fat biofuel, and their 50% (volume) blends in Jet A were studied over a range of throttle settings. The addition of biofuel resulted in a reduction in static thrust and thrust-specific fuel consumption, and increased thermal efficiency. The CO and NO emissions from the Turbine were reduced with the biofuel blends. The results suggest that an optimum mixture may be found that reduces pollutant emissions while producing the desired thrust. This study demonstrates that biofuels may serve as viable supplements to petroleum-based fuels.

Susan E Cunningham - One of the best experts on this subject based on the ideXlab platform.

  • damage tolerance based life prediction in gas Turbine Engine blades under vibratory high cycle fatigue
    Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 1997
    Co-Authors: D P Walls, Robert E Delaneuville, Susan E Cunningham
    Abstract:

    A novel fracture mechanics approach has been used to predict crack propagation lives in gas Turbine Engine blades subjected to vibratory high cycle fatigue (HCF). The vibratory loading included both a resonant mode and a nonresonant mode, with one blade subjected to only the nonresonant mode and another blade to both modes. A life prediction algorithm was utilized to predict HCF propagation lives for each case. The life prediction system incorporates a boundary integral element (BIE) derived hybrid stress intensity solution, which accounts for the transition from a surface crack to corner crack to edge crack. It also includes a derivation of threshold crack length from threshold stress intensity factors to give crack size limits for no propagation. The stress intensity solution was calibrated for crack aspect ratios measured directly from the fracture surfaces. The model demonstrates the ability to correlate predicted missions to failure with values deduced from fractographic analysis. This analysis helps to validate the use of fracture mechanics approaches for assessing damage tolerance in gas Turbine Engine components subjected to combined steady and vibratory stresses.

  • damage tolerance based life prediction in gas Turbine Engine blades under vibratory high cycle fatigue
    Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls Diagnostics and Instrumentation; Education; IGTI Scholar, 1995
    Co-Authors: D P Walls, Robert E Delaneuville, Susan E Cunningham
    Abstract:

    A novel fracture mechanics approach has been used to predict crack propagation lives in gas Turbine Engine blades subjected to vibratory high cycle fatigue (HCF). The vibratory loading included both a resonant mode and a non-resonant mode, with one blade subjected to only the non-resonant mode and another blade to both modes. A life prediction algorithm was utilized to predict HCF propagation lives for each case. The life prediction system incorporates a boundary integral element (BIE) derived hybrid stress intensity solution which accounts for the transition from a surface crack to corner crack to edge crack. It also includes a derivation of threshold crack length from threshold stress intensity factors to give crack size limits for no propagation. The stress intensity solution was calibrated for crack aspect ratios measured directly from the fracture surfaces. The model demonstrates the ability to correlate predicted missions to failure with values deduced from fractographic analysis. This analysis helps to validate the use of fracture mechanics approaches for assessing damage tolerance in gas Turbine Engine components subjected to combined steady and vibratory stresses.Copyright © 1995 by ASME

Thomas Ory Moniz - One of the best experts on this subject based on the ideXlab platform.

  • variable torque split aircraft gas Turbine Engine counter rotating low pressure Turbines
    2002
    Co-Authors: John Lewis Baughman, Robert Joseph Orlando, Thomas Ory Moniz
    Abstract:

    An aircraft gas Turbine Engine includes a low pressure Turbine having a low pressure Turbine flowpath and low pressure inner and outer shaft Turbines with counter rotatable low pressure inner and outer shaft Turbine rotors, respectively. The low pressure inner and outer shaft Turbine rotors include low pressure first and second Turbine blade rows disposed across the Turbine flowpath which are drivingly connected to first and second fan blade rows by low pressure inner and outer shafts, respectively. At least one row of low pressure variable vanes is operably disposed across the low pressure Turbine flowpath between the low pressure inner and outer shaft Turbines. The low pressure first Turbine blade rows of the low pressure inner shaft Turbine may be in tandem with or interdigitated with the second Turbine blade rows of the low pressure outer shaft Turbines.

  • counter rotating fan aircraft gas Turbine Engine with aft booster
    2002
    Co-Authors: Robert Joseph Orlando, Thomas Ory Moniz
    Abstract:

    A gas Turbine Engine Turbine assembly includes a high pressure spool having a high pressure Turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable about an Engine centerline. A low pressure Turbine has counter rotatable low pressure inner and outer shaft Turbines drivingly connected to coaxial low pressure inner and outer shafts respectively which are at least in part rotatably disposed co-axial with and radially inwardly of the high pressure spool. The low pressure inner shaft Turbine is drivingly connected to a forward fan blade row by the low pressure inner shaft. The low pressure outer shaft Turbine is drivingly connected to a aft fan blade row by the low pressure outer shaft. A single direction of rotation booster is drivenly connected to the low pressure outer shaft and axially located aft and downstream of the aft fan blade row.

  • aircraft gas Turbine Engine with control vanes for counter rotating low pressure Turbines
    2002
    Co-Authors: Robert Joseph Orlando, Thomas Ory Moniz
    Abstract:

    An aircraft gas Turbine Engine includes a low pressure Turbine having a low pressure Turbine flowpath and counter rotatable low pressure inner and outer shaft rotors having inner and outer shafts, respectively. The low pressure inner and outer shaft rotors include low pressure first and second Turbine blade rows disposed across the Turbine flowpath and drivingly connected to first and second fan blade rows by low pressure inner and outer shafts, respectively. At least one of the low pressure first and second Turbine blade rows is interdigitated with an adjacent pair of one of the Turbine blade rows. At least one row of non-rotatable low pressure vanes is disposed across the low pressure Turbine flowpath between a non interdigitated adjacent pair of one of the Turbine blade rows.

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