Gas turbine annular combustor with radial dilution air injection
This patent describes a radial flow gas turbine. It comprises: a rotor including turbine blades and a nozzle adjacent the turbine blades, the nozzle being adapted to direct hot gases at the turbine blades to cause rotation of the rotor; an annular combustor about the rotor and having a combustor outlet leading to the nozzle, the annular combustor having spaced inner and outer walls connected by a generally radially extending wall, the annular combustor including a combustion annulus defined by the inner, outer and radially extending walls upstream of the outlet; a dilution air annulus disposed downstream of the combustion annulus and immediately radially outwardly of the nozzle axially adjacent to and immediately downstream of the combustor outlet of the annular combustion; and a housing substantially surrounding the annular combustor in spaced relation to the inner, outer and radially extending walls thereof, the housing and walls together defining at least a portion of a dilution air flow path having a compressed air inlet in communication with a compressor for supplying dilution air at one end thereof, a turbine nozzle shroud and the inner wall defining the remainder of the dilution air flow path, the compressed air outlet injecting dilution air directly across the combustor outlet toward the compressed air inlet, the illusion air being injected into the hot gases at generally a right angle thereto assist hot gases approach the combustor outlet, the compressed air outlet being in communication with the dilution air annulus directly through the combustor outlet of the annular combustor downstream of the combustion annulus.
- Assignee:
- Sundstrand Corp., Rockford, IL (United States)
- Patent Number(s):
- US 5058375; A
- Application Number:
- PPN: US 7-541489A
- OSTI ID:
- 5637846
- Resource Relation:
- Patent File Date: 21 Jun 1990
- Country of Publication:
- United States
- Language:
- English
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