Grant: Collaborative Research and Development Grants
Royal Military College of Canada
$32,700.00
Internal flow investigations on the Rolls Royce Allison T-63 engine
FY 2011-12
Summary
A collaborative investigation has been initiated by the Royal Military College of Canada (RMC) and Standard Aero Limited (SAL) of Winnipeg. The objectives of the project are to study compressor instabilities, to investigate the internal aerodynamic characteristics of the major engine stages and their influences on downstream components, and to quantify the temperature profile at the exit of a combustion chamber. The program will initially explore rotating compressor stall in the axial stage of a Rolls Royce Allison A250 gas turbine. Three follow-on research thrusts will explore the centrifugal stage on the same rig, while an existing combustion chamber test rig will be used to explore the effects of inlet disturbances on the combustion chamber. Finally, compressor discharge ducts will be surveyed and modelled to determine influences between the two major components. SAL is a major global overhauler and engineering developer of the A250 gas turbine engine and the insight gained will be applied to improving their role as an engineering service provider. HQP specifically post-graduate students will be drawn from SAL employees; other students will be attracted from conventional sources.
The first phase of the project will see the completion of an internal combustion engine-driven, axial compressor rig, from which pre-stall signals will be recorded from high speed pressure transducers. Stall will be initiated using a throttle, and high speed data acquisition will be used to record the events. The rig has been designed to allow the centrifugal compressor stage to be independently tested in a follow-on phase. This research is a natural fit for the RMC research group which has substantial experience with ambient rigs and engine representative conditions. With the rig, it will be possible to investigate flow and combustion instabilities in great detail. Data collected will support parallel computational and numerical studies. The first phase of this project is underway; the first of five post-graduate students has entered the research phase and is expected to graduate in the winter of 2008.
Program
Collaborative Research and Development Grants
Recipient
Location
Ontario, Canada
Recipient Type
Academia
Type
Grant
Source
NSERC's Awards Data
As published
Application id
357143-2007
Name nom
Allan, William
Department département
Mechanical Engineering
Organization id
30
Institution établissement
Royal Military College of Canada
Province en
Ontario
Province fr
Ontario
Country en
CANADA
Country fr
CANADA
Fiscal year exercice financier
2011
Competition year année de concours
2007
Award amount
32700
Program id
CRDPJ
Program nane en
Collaborative Research and Development Grants
Program name fr
Subventions de recherche et développement coopérative
Group en
Research partnerships programs
Group fr
Programmes de partenariat
Committee code
96
Committee name en
RPP Internal Decision Cttee
Committee name fr
Cté de décision interne - PPR
Area of application code
703
Area of application group en
Transportation systems and services
Area of application group fr
Services et systèmes de transport
Area of application en
Aerospace
Area of application fr
Aérospatial
Research subject code
2108
Research subject group en
Mechanical engineering
Research subject group fr
Génie mécanique
Research subject en
Aerospace, aeronautical and automotive engineering
Research subject fr
Génie aérospatial, aéronautique et automobile
Partie
3
Nb partie
5
Application title
Internal flow investigations on the Rolls Royce Allison T-63 engine
Keyword
NSERC
Application summary
A collaborative investigation has been initiated by the Royal Military College of Canada (RMC) and Standard Aero Limited (SAL) of Winnipeg. The objectives of the project are to study compressor instabilities, to investigate the internal aerodynamic characteristics of the major engine stages and their influences on downstream components, and to quantify the temperature profile at the exit of a combustion chamber. The program will initially explore rotating compressor stall in the axial stage of a Rolls Royce Allison A250 gas turbine. Three follow-on research thrusts will explore the centrifugal stage on the same rig, while an existing combustion chamber test rig will be used to explore the effects of inlet disturbances on the combustion chamber. Finally, compressor discharge ducts will be surveyed and modelled to determine influences between the two major components. SAL is a major global overhauler and engineering developer of the A250 gas turbine engine and the insight gained will be applied to improving their role as an engineering service provider. HQP specifically post-graduate students will be drawn from SAL employees; other students will be attracted from conventional sources.
The first phase of the project will see the completion of an internal combustion engine-driven, axial compressor rig, from which pre-stall signals will be recorded from high speed pressure transducers. Stall will be initiated using a throttle, and high speed data acquisition will be used to record the events. The rig has been designed to allow the centrifugal compressor stage to be independently tested in a follow-on phase. This research is a natural fit for the RMC research group which has substantial experience with ambient rigs and engine representative conditions. With the rig, it will be possible to investigate flow and combustion instabilities in great detail. Data collected will support parallel computational and numerical studies. The first phase of this project is underway; the first of five post-graduate students has entered the research phase and is expected to graduate in the winter of 2008.
