Power plants – Combustion products used as motive fluid – Plural combustion products generators in ring coaxial with...
Patent
1993-10-01
1994-10-11
Thorpe, Timothy S.
Power plants
Combustion products used as motive fluid
Plural combustion products generators in ring coaxial with...
60 3975, F02C 314
Patent
active
053535863
DESCRIPTION:
BRIEF SUMMARY
This is a 371 of PCT/GB92/00017, filed Jan. 6, 1992.
The present invention relates to combustion chamber assemblies, particularly for gas turbine engines.
Currently many industrial gas turbine engines use annular or can-annular combustion chambers in an axial flow gas turbine engine. In annular and can-annular combustion chamber assemblies, inner and outer annular casings are provided coaxially around the annular, or can-annular, combustion chamber assembly. The inner casing interconnects the compressor casing and the outer platforms of the nozzle guide vanes, to tie the thermal expansion of the compressor casing and the thermal expansion of the nozzle guide vane platforms together to maintain their relative locations, and to enable nozzle guide vane tilt reduction with increasing temperature. The inner casing is secured to the outer casing to provide outer location of the compressor and turbine stator vanes. The inner and outer annular casings also define an annular passageway for the flow of cooling fluid, bled from the compressor, to the turbine.
In order to meet the emission level requirement for low emission industrial gas turbine engines, the combustion chamber volume has been increased. The requirement to increase the volume of the combustion chamber assembly whilst incorporating the combustion chamber assembly in the same axial length has necessitated the use of a plurality of tubular combustion chambers, whose longitudinal axes are arranged in a generally radial direction with respect to the longitudinal axis of the gas turbine engine. The upstream, or inlet, ends of the tubular combustion chambers are at the radially outer end, and transition ducts connect the downstream, or outlet, ends of the tubular combustion chambers with the nozzle guide vanes to discharge the hot combustion gases axially into the turbine section of the gas turbine engine.
Thus the provision of the tubular combustion chambers, whose axes are arranged generally radially with respect to the longitudinal axis of the gas turbine engine, prevents the use of an inner annular casing for interconnecting the compressor casing and the outer platforms of the nozzle guide vanes, to tie the thermal expansion of the compressor casing and the thermal expansion of the nozzle guide vane platforms together to maintain their relative locations, and to enable nozzle guide vane tilt reduction with increasing temperature. Also the provision of an outer location of the compressor and turbine stator vanes and a cooling passage for the flow of cooling fluid to the turbine is prevented.
Accordingly the present invention seeks to provide a combustion chamber assembly comprising a plurality of circumferentially spaced tubular combustion chambers which have their axes arranged generally in a radial direction with respect to a longitudinal axis which overcomes the above mentioned problems.
Accordingly the present invention provides a combustion chamber assembly for a gas turbine engine comprising a plurality of elongate combustion chambers extending generally radially with respect to a longitudinal axis of the gas turbine engine, the radially inner ends of the elongate combustion chambers are arranged to discharge combustion gases into a turbine through an annular array of nozzle guide vanes, a first stiff frustoconical casing member located at the upstream end of the combustion chamber assembly, a second stiff frustoconical casing member connected to the nozzle guide vane array at the downstream end of the combustion chamber assembly, a plurality of hollow members with opposing ends secured to the first and second frustoconical casing members and extending between adjacent ones of the combustion chambers to transfer tensile and compressive stresses through the assembly between the first and second frustoconical casing members, the ends of the hollow members are connected to passage means associated with the frustoconical casing members for the transfer of cooling fluid across the assembly.
Preferably the smaller diameter end of the first frustoconical
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Griffin Arthur B.
Taylor David H.
Rolls-Royce plc
Thorpe Timothy S.
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