The Experts below are selected from a list of 306 Experts worldwide ranked by ideXlab platform
Edward H. Robey - One of the best experts on this subject based on the ideXlab platform.
-
Effect of Fuel System Impedance Mismatch on Combustion Dynamics
Journal of Engineering for Gas Turbines and Power, 2008Co-Authors: Geo A. Richards, Edward H. RobeyAbstract:Combustion dynamics are a challenging problem in the design and operation of premixed gas turbine combustors. In premixed combustors, pressure oscillations created by the flame dynamic response can lead to damaging pressure oscillations. These dynamics are typically controlled by designing the combustor to achieve stable operation for planned conditions, but dynamics may still occur with minor changes in ambient operating conditions, or Fuel composition. In these situations, pilot flames, or adjustment to Fuel flow splits can be used to stabilize the combustor, but often with a compromise in emissions performance. As an alternative to purely passive design changes, prior studies have demonstrated that adjustment to the Fuel System impedance can be used to stabilize combustion. Prior studies have considered just the response of individual Fuel injector and combustor. However, in practical combustion Systems, multiple Fuel injectors are used. In this situation, individual injector impedance can be modified to produce a different dynamic response from individual flames. The resulting impedance mismatch prevents all injectors from strongly coupling to the same acoustic mode. In principle, this mismatch should reduce the amplitude of dynamics, and may expand the operating margin for stable combustion conditions. In this paper, a 30 kW laboratory combustor with two premixed Fuel injectors is used to study the effect of impedance mismatch on combustion stability. The two Fuel injectors are equipped with variable geometry resonators that allow a survey of dynamic stability while changing the impedance of the individual Fuel Systems. Results demonstrate that a wide variation in dynamic response can be achieved by combining different impedence Fuel injectors. A baseline 7% RMS pressure oscillation was reduced to less than 3% by mismatching the Fuel impedance.Copyright © 2005 by ASME
-
Effect of Fuel System Impedance Mismatch on Combustion Dynamics
Volume 2: Turbo Expo 2005, 2005Co-Authors: Geo A. Richards, Edward H. RobeyAbstract:Combustion dynamics are a challenging problem in the design and operation of premixed gas turbine combustors. In premixed combustors, pressure oscillations created by the flame dynamic response can lead to damaging pressure oscillations. These dynamics are typically controlled by designing the combustor to achieve stable operation for planned conditions, but dynamics may still occur with minor changes in ambient operating conditions, or Fuel composition. In these situations, pilot flames, or adjustment to Fuel flow splits can be used to stabilize the combustor, but often with a compromise in emissions performance. As an alternative to purely passive design changes, prior studies have demonstrated that adjustment to the Fuel System impedance can be used to stabilize combustion. Prior studies have considered just the response of individual Fuel injector and combustor. However, in practical combustion Systems, multiple Fuel injectors are used. In this situation, individual injector impedance can be modified to produce a different dynamic response from individual flames. The resulting impedance mismatch prevents all injectors from strongly coupling to the same acoustic mode. In principle, this mismatch should reduce the amplitude of dynamics, and may expand the operating margin for stable combustion conditions. In this paper, a 30 kW laboratory combustor with two premixed Fuel injectors is used to study the effect of impedance mismatch on combustion stability. The two Fuel injectors are equipped with variable geometry resonators that allow a survey of dynamic stability while changing the impedance of the individual Fuel Systems. Results demonstrate that a wide variation in dynamic response can be achieved by combining different impedence Fuel injectors. A baseline 7% RMS pressure oscillation was reduced to less than 3% by mismatching the Fuel impedance.
Hampus Gavel - One of the best experts on this subject based on the ideXlab platform.
-
An Algorithmic Morphology Matrix for Aircraft Fuel System Design
2008Co-Authors: Hampus Gavel, Johan Andersson, Bjorn JohanssonAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time. This is done by means of illustrative examples of how optimization and the use of matrix methods, such as the morphological matrix, house of quality and the design structure matrix, have been developed and implemented at Saab Aerospace in the conceptual design of aircraft Fuel Systems. The methods introduce automation early in the development process and increase understanding of how top requirements regarding the aircraft level impact low-level engineering parameters such as pipe diameter, pump size, etc. The morphological matrix and the house of quality matrix are quantified, which opens up for use of design optimization and probabilistic design. The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minimize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the model to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders’ expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
-
Aircraft Fuel System synthesis aided by interactive morphology and optimization
45th AIAA Aerospace Sciences Meeting and Exhibit, 2007Co-Authors: Hampus Gavel, Bjorn Johansson, Saab Aerosystems, Johan Ölvander, Petter KrusAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time. This is done by means of illustrative examples of how optimization and the use of matrix methods, such as the morphological matrix, house of quality and the design structure matrix, have been developed and implemented at Saab Aerospace in the conceptual design of aircraft Fuel Systems. The methods introduce automation early in the development process and increase understanding of how top requirements regarding the aircraft level impact low-level engineering parameters such as pipe diameter, pump size, etc. The morphological matrix and the house of quality matrix are quantified, which opens up for use of design optimization and probabilistic design. The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minimize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the model to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders’ expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
-
On aircraft Fuel Systems : conceptual design and modeling
2007Co-Authors: Hampus GavelAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodolo ...
-
probabilistic design in the conceptual phase of an aircraft Fuel System
2005Co-Authors: Hampus Gavel, Petter Krus, Johan Andersson, Bjorn JohanssonAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time. This is done by means of illustrative examples of how optimization and the use of matrix methods, such as the morphological matrix, house of quality and the design structure matrix, have been developed and implemented at Saab Aerospace in the conceptual design of aircraft Fuel Systems. The methods introduce automation early in the development process and increase understanding of how top requirements regarding the aircraft level impact low-level engineering parameters such as pipe diameter, pump size, etc. The morphological matrix and the house of quality matrix are quantified, which opens up for use of design optimization and probabilistic design. The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minimize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the model to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders’ expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
-
On Aircraft Fuel System Conceptual Design - Conceptual Evaluation and System modeling
2004Co-Authors: Hampus GavelAbstract:THE LARGEST AND most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodolo ...
Geo A. Richards - One of the best experts on this subject based on the ideXlab platform.
-
Effect of Fuel System Impedance Mismatch on Combustion Dynamics
Journal of Engineering for Gas Turbines and Power, 2008Co-Authors: Geo A. Richards, Edward H. RobeyAbstract:Combustion dynamics are a challenging problem in the design and operation of premixed gas turbine combustors. In premixed combustors, pressure oscillations created by the flame dynamic response can lead to damaging pressure oscillations. These dynamics are typically controlled by designing the combustor to achieve stable operation for planned conditions, but dynamics may still occur with minor changes in ambient operating conditions, or Fuel composition. In these situations, pilot flames, or adjustment to Fuel flow splits can be used to stabilize the combustor, but often with a compromise in emissions performance. As an alternative to purely passive design changes, prior studies have demonstrated that adjustment to the Fuel System impedance can be used to stabilize combustion. Prior studies have considered just the response of individual Fuel injector and combustor. However, in practical combustion Systems, multiple Fuel injectors are used. In this situation, individual injector impedance can be modified to produce a different dynamic response from individual flames. The resulting impedance mismatch prevents all injectors from strongly coupling to the same acoustic mode. In principle, this mismatch should reduce the amplitude of dynamics, and may expand the operating margin for stable combustion conditions. In this paper, a 30 kW laboratory combustor with two premixed Fuel injectors is used to study the effect of impedance mismatch on combustion stability. The two Fuel injectors are equipped with variable geometry resonators that allow a survey of dynamic stability while changing the impedance of the individual Fuel Systems. Results demonstrate that a wide variation in dynamic response can be achieved by combining different impedence Fuel injectors. A baseline 7% RMS pressure oscillation was reduced to less than 3% by mismatching the Fuel impedance.Copyright © 2005 by ASME
-
Effect of Fuel System Impedance Mismatch on Combustion Dynamics
Volume 2: Turbo Expo 2005, 2005Co-Authors: Geo A. Richards, Edward H. RobeyAbstract:Combustion dynamics are a challenging problem in the design and operation of premixed gas turbine combustors. In premixed combustors, pressure oscillations created by the flame dynamic response can lead to damaging pressure oscillations. These dynamics are typically controlled by designing the combustor to achieve stable operation for planned conditions, but dynamics may still occur with minor changes in ambient operating conditions, or Fuel composition. In these situations, pilot flames, or adjustment to Fuel flow splits can be used to stabilize the combustor, but often with a compromise in emissions performance. As an alternative to purely passive design changes, prior studies have demonstrated that adjustment to the Fuel System impedance can be used to stabilize combustion. Prior studies have considered just the response of individual Fuel injector and combustor. However, in practical combustion Systems, multiple Fuel injectors are used. In this situation, individual injector impedance can be modified to produce a different dynamic response from individual flames. The resulting impedance mismatch prevents all injectors from strongly coupling to the same acoustic mode. In principle, this mismatch should reduce the amplitude of dynamics, and may expand the operating margin for stable combustion conditions. In this paper, a 30 kW laboratory combustor with two premixed Fuel injectors is used to study the effect of impedance mismatch on combustion stability. The two Fuel injectors are equipped with variable geometry resonators that allow a survey of dynamic stability while changing the impedance of the individual Fuel Systems. Results demonstrate that a wide variation in dynamic response can be achieved by combining different impedence Fuel injectors. A baseline 7% RMS pressure oscillation was reduced to less than 3% by mismatching the Fuel impedance.
Bjorn Johansson - One of the best experts on this subject based on the ideXlab platform.
-
An Algorithmic Morphology Matrix for Aircraft Fuel System Design
2008Co-Authors: Hampus Gavel, Johan Andersson, Bjorn JohanssonAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time. This is done by means of illustrative examples of how optimization and the use of matrix methods, such as the morphological matrix, house of quality and the design structure matrix, have been developed and implemented at Saab Aerospace in the conceptual design of aircraft Fuel Systems. The methods introduce automation early in the development process and increase understanding of how top requirements regarding the aircraft level impact low-level engineering parameters such as pipe diameter, pump size, etc. The morphological matrix and the house of quality matrix are quantified, which opens up for use of design optimization and probabilistic design. The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minimize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the model to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders’ expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
-
Aircraft Fuel System synthesis aided by interactive morphology and optimization
45th AIAA Aerospace Sciences Meeting and Exhibit, 2007Co-Authors: Hampus Gavel, Bjorn Johansson, Saab Aerosystems, Johan Ölvander, Petter KrusAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time. This is done by means of illustrative examples of how optimization and the use of matrix methods, such as the morphological matrix, house of quality and the design structure matrix, have been developed and implemented at Saab Aerospace in the conceptual design of aircraft Fuel Systems. The methods introduce automation early in the development process and increase understanding of how top requirements regarding the aircraft level impact low-level engineering parameters such as pipe diameter, pump size, etc. The morphological matrix and the house of quality matrix are quantified, which opens up for use of design optimization and probabilistic design. The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minimize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the model to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders’ expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
-
probabilistic design in the conceptual phase of an aircraft Fuel System
2005Co-Authors: Hampus Gavel, Petter Krus, Johan Andersson, Bjorn JohanssonAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time. This is done by means of illustrative examples of how optimization and the use of matrix methods, such as the morphological matrix, house of quality and the design structure matrix, have been developed and implemented at Saab Aerospace in the conceptual design of aircraft Fuel Systems. The methods introduce automation early in the development process and increase understanding of how top requirements regarding the aircraft level impact low-level engineering parameters such as pipe diameter, pump size, etc. The morphological matrix and the house of quality matrix are quantified, which opens up for use of design optimization and probabilistic design. The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minimize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the model to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders’ expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
Johan Andersson - One of the best experts on this subject based on the ideXlab platform.
-
An Algorithmic Morphology Matrix for Aircraft Fuel System Design
2008Co-Authors: Hampus Gavel, Johan Andersson, Bjorn JohanssonAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time. This is done by means of illustrative examples of how optimization and the use of matrix methods, such as the morphological matrix, house of quality and the design structure matrix, have been developed and implemented at Saab Aerospace in the conceptual design of aircraft Fuel Systems. The methods introduce automation early in the development process and increase understanding of how top requirements regarding the aircraft level impact low-level engineering parameters such as pipe diameter, pump size, etc. The morphological matrix and the house of quality matrix are quantified, which opens up for use of design optimization and probabilistic design. The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minimize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the model to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders’ expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
-
probabilistic design in the conceptual phase of an aircraft Fuel System
2005Co-Authors: Hampus Gavel, Petter Krus, Johan Andersson, Bjorn JohanssonAbstract:The largest and most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time. This is done by means of illustrative examples of how optimization and the use of matrix methods, such as the morphological matrix, house of quality and the design structure matrix, have been developed and implemented at Saab Aerospace in the conceptual design of aircraft Fuel Systems. The methods introduce automation early in the development process and increase understanding of how top requirements regarding the aircraft level impact low-level engineering parameters such as pipe diameter, pump size, etc. The morphological matrix and the house of quality matrix are quantified, which opens up for use of design optimization and probabilistic design. The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minimize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the model to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders’ expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
-
Using Optimization as a Tool in Fuel System Conceptual Design
SAE Technical Paper Series, 2003Co-Authors: Hampus Gavel, Johan AnderssonAbstract:THE LARGEST AND most important fluid System in an aircraft is the Fuel System. Obviously, future aircraft projects involve the design of Fuel System to some degree. In this project design methodologies for aircraft Fuel Systems are studied, with the aim to shortening the System development time.This is done by means of illustrative examples of how optimization and the use of matrix methods have been developed and implemented at Saab Aerospace in the conceptual design of ale Fuel Systems. The methods introduces automation early in the development process and increase understanding of how top requirements on the ale level impact low-level engineering parameters such as pipe diameter, pump size, etc.The thesis also discusses a Systematic approach when building a large simulation model of a fluid System where the objective is to minirnize the development time by applying a strategy that enables parallel development and collaborative engineering, and also by building the mode! to the correct level of detail. By correct level of detail is meant the level that yields a simulation outcome that meets the stakeholders' expectations. The experienced gained at Saab in building a simulation model, mainly from the Gripen Fuel System, but also the accumulated experience from other System models, is condensed and fitted into an overall process.
