Author: Rodrick V. Chima
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Book Description
The flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data. Tip clearance effects were modeled both by gridding the clearance gap and by using a simple periodicity model across the ungridded gap. The simple model was run with both the full gap height, and with half the gap height to simulate a vena-contracta effect. Comparisons between computed and measured performance maps and downstream profiles were used to validate the models and to assess the effects of gap height on the simple clearance model. Recommendations were made concerning the use of the simple clearance model. Detailed comparisons were made between the gridded clearance gap solution and the laser anemometer data near the tip at two operating points. The computer results agreed fairly well with the data but overpredicted the extent of the casing separation and underpredicted the wake decay rate. The computations were then used to describe the interaction of the tip vortex, the passage shock, and the casing boundary layer.
Calculation of Tip Clearance Effects in a Transonic Compressor Rotor
Author: Rodrick V. Chima
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Book Description
The flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data. Tip clearance effects were modeled both by gridding the clearance gap and by using a simple periodicity model across the ungridded gap. The simple model was run with both the full gap height, and with half the gap height to simulate a vena-contracta effect. Comparisons between computed and measured performance maps and downstream profiles were used to validate the models and to assess the effects of gap height on the simple clearance model. Recommendations were made concerning the use of the simple clearance model. Detailed comparisons were made between the gridded clearance gap solution and the laser anemometer data near the tip at two operating points. The computer results agreed fairly well with the data but overpredicted the extent of the casing separation and underpredicted the wake decay rate. The computations were then used to describe the interaction of the tip vortex, the passage shock, and the casing boundary layer.
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Book Description
The flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data. Tip clearance effects were modeled both by gridding the clearance gap and by using a simple periodicity model across the ungridded gap. The simple model was run with both the full gap height, and with half the gap height to simulate a vena-contracta effect. Comparisons between computed and measured performance maps and downstream profiles were used to validate the models and to assess the effects of gap height on the simple clearance model. Recommendations were made concerning the use of the simple clearance model. Detailed comparisons were made between the gridded clearance gap solution and the laser anemometer data near the tip at two operating points. The computer results agreed fairly well with the data but overpredicted the extent of the casing separation and underpredicted the wake decay rate. The computations were then used to describe the interaction of the tip vortex, the passage shock, and the casing boundary layer.
Advances in Gas Turbine Technology
Author: Ernesto Benini
Publisher: BoD – Books on Demand
ISBN: 9533076119
Category : Science
Languages : en
Pages : 542
Book Description
Gas turbine engines will still represent a key technology in the next 20-year energy scenarios, either in stand-alone applications or in combination with other power generation equipment. This book intends in fact to provide an updated picture as well as a perspective vision of some of the major improvements that characterize the gas turbine technology in different applications, from marine and aircraft propulsion to industrial and stationary power generation. Therefore, the target audience for it involves design, analyst, materials and maintenance engineers. Also manufacturers, researchers and scientists will benefit from the timely and accurate information provided in this volume. The book is organized into five main sections including 21 chapters overall: (I) Aero and Marine Gas Turbines, (II) Gas Turbine Systems, (III) Heat Transfer, (IV) Combustion and (V) Materials and Fabrication.
Publisher: BoD – Books on Demand
ISBN: 9533076119
Category : Science
Languages : en
Pages : 542
Book Description
Gas turbine engines will still represent a key technology in the next 20-year energy scenarios, either in stand-alone applications or in combination with other power generation equipment. This book intends in fact to provide an updated picture as well as a perspective vision of some of the major improvements that characterize the gas turbine technology in different applications, from marine and aircraft propulsion to industrial and stationary power generation. Therefore, the target audience for it involves design, analyst, materials and maintenance engineers. Also manufacturers, researchers and scientists will benefit from the timely and accurate information provided in this volume. The book is organized into five main sections including 21 chapters overall: (I) Aero and Marine Gas Turbines, (II) Gas Turbine Systems, (III) Heat Transfer, (IV) Combustion and (V) Materials and Fabrication.
Blockage Development in a Transonic, Axial Compressor Rotor
Author: Kenneth L. Suder
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Orlando, FL, Jun 2 - Jun 5, 1997.
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Orlando, FL, Jun 2 - Jun 5, 1997.
ASME Technical Papers
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 488
Book Description
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 488
Book Description
Paper
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 506
Book Description
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 506
Book Description
Design of a Low Aspect Ratio Transonic Compressor Stage Using CFD Techniques
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit: 2000-3200 - 2000-3249
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 586
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 586
Book Description
Effects of Upstream Wake Phasing on the Performance of Transonic Compressors
Author: Sean Patrick Rock Nolan
Publisher:
ISBN:
Category :
Languages : en
Pages : 100
Book Description
The effect of the upstream wake phase on the work input (i.e., rise in stagnation enthalpy across the blade row) of a transonic rotor is examined computationally and analytically. It is found that the compressor work depends on the path followed by the wake vortices as they travel through the rotor passage. There can be an important impact on time-mean performance when the time-dependent circulation of the shed vortices in the wake is phase-locked to the rotor position. For the configurations tested, the calculated change in time-mean work input was approximately three percent. The effect on work input is explained in terms of the influence of the time-mean relative stagnation pressure nonuniformity associated with the unsteady (but phase-locked) wake vortex flow field. Changes in vortex path mean that the position of this nonuniformity is altered relative to the rotor. There is lower pressure rise, and thus lower work, when the rotor blade is embedded in the region of low time-mean relative stagnation pressure than when it is immersed in a region of high relative stagnation pressure. In addition to this essentially two-dimensional effect, it is demonstrated that the locations of the wake vortex paths can have substantial effect on the tip clearance flow, implying potential impact on pressure rise capability and rotor stability limits. Model calculations are given to show the magnitude and nature of this phenomenon.
Publisher:
ISBN:
Category :
Languages : en
Pages : 100
Book Description
The effect of the upstream wake phase on the work input (i.e., rise in stagnation enthalpy across the blade row) of a transonic rotor is examined computationally and analytically. It is found that the compressor work depends on the path followed by the wake vortices as they travel through the rotor passage. There can be an important impact on time-mean performance when the time-dependent circulation of the shed vortices in the wake is phase-locked to the rotor position. For the configurations tested, the calculated change in time-mean work input was approximately three percent. The effect on work input is explained in terms of the influence of the time-mean relative stagnation pressure nonuniformity associated with the unsteady (but phase-locked) wake vortex flow field. Changes in vortex path mean that the position of this nonuniformity is altered relative to the rotor. There is lower pressure rise, and thus lower work, when the rotor blade is embedded in the region of low time-mean relative stagnation pressure than when it is immersed in a region of high relative stagnation pressure. In addition to this essentially two-dimensional effect, it is demonstrated that the locations of the wake vortex paths can have substantial effect on the tip clearance flow, implying potential impact on pressure rise capability and rotor stability limits. Model calculations are given to show the magnitude and nature of this phenomenon.
NASA Technical Paper
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 92
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 92
Book Description
33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 562
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 562
Book Description