An experimental and computational investigation has been undertaken into the effects of deterioration of the first stage rotor shroud knife-edge seal clearance in a two-stage turbine which has engine representative cavity geometries. Four values of deterioration were investigated which cover the new-condition to old-condition knife-edge seal clearance. Measurements within the first stage rotor shroud cavity show that whilst the leakage mass flow rate increases with deterioration, the angle at which the leakage flow approaches the downstream stator is essentially fixed and independent of the flow coefficient. This is in agreement with a simple over-tip leakage model. Because of the engine representative cavity geometry, the over-shroud leaka...
The secondary flow increases the loss and changes the flow incidence in the downstream blade row. To...
As performance improvements of compressors become more difficult to obtain, the optimization of stat...
In gas turbine and aeroengine, the rim seal is set between the turbine stator and rotor to prevent i...
Abstract An experimental and computational investigation has been undertaken into the...
An experimental and computational investigation has been undertaken into the effects of deterioratio...
As part of the drive towards achieving net-zero flight by 2050, the development of ultra-high bypass...
Thesis: Ph. D., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2015.Th...
AbstractIn modern gas turbines, rim seal located between the stator-disc and rotor-disc is used to p...
This degree project in applied physics studies the tip gap flows over the rotor blades of a high-pre...
In this paper, the effect of seal clearance on the efficiency of a turbine with a shrouded rotor is ...
A study of the three-dimensional stator-rotor interaction in a turbine stage is presented. Experimen...
The area between the stationary and rotating hub side endwall segments in axial turbines is featured...
The impact of the wheelspace cavity purge flow on a high-pressure axial low-reaction turbine stage i...
In modern gas turbines or jet engines, the ingestion of hot gas through the hub-side gap between rot...
This paper presents the results of the experimental and computational research programs to investiga...
The secondary flow increases the loss and changes the flow incidence in the downstream blade row. To...
As performance improvements of compressors become more difficult to obtain, the optimization of stat...
In gas turbine and aeroengine, the rim seal is set between the turbine stator and rotor to prevent i...
Abstract An experimental and computational investigation has been undertaken into the...
An experimental and computational investigation has been undertaken into the effects of deterioratio...
As part of the drive towards achieving net-zero flight by 2050, the development of ultra-high bypass...
Thesis: Ph. D., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2015.Th...
AbstractIn modern gas turbines, rim seal located between the stator-disc and rotor-disc is used to p...
This degree project in applied physics studies the tip gap flows over the rotor blades of a high-pre...
In this paper, the effect of seal clearance on the efficiency of a turbine with a shrouded rotor is ...
A study of the three-dimensional stator-rotor interaction in a turbine stage is presented. Experimen...
The area between the stationary and rotating hub side endwall segments in axial turbines is featured...
The impact of the wheelspace cavity purge flow on a high-pressure axial low-reaction turbine stage i...
In modern gas turbines or jet engines, the ingestion of hot gas through the hub-side gap between rot...
This paper presents the results of the experimental and computational research programs to investiga...
The secondary flow increases the loss and changes the flow incidence in the downstream blade row. To...
As performance improvements of compressors become more difficult to obtain, the optimization of stat...
In gas turbine and aeroengine, the rim seal is set between the turbine stator and rotor to prevent i...