Combustion selective temperature dilution
In a gas turbine engine having a hot gas flowing in an annular path partially defined by inner and outer liners of a combustor and inner and outer vane shrouds, the combustor including at its upstream end injectors for admitting an original mixture of air and fuel to the upstream end of the combustor for burning of the mixture in the combustor, the improvement is described comprising: circumferentially spaced-apart stationary turbine vanes disposed in the hot gas flow path downstream of the combustor; circumferentially spaced-apart dilution apertures disposed in the combustor downstream of the injectors, upstream of the turbine vanes and in axial alignment with leading edges of the turbine vanes, for admitting dilution air into the combustor for mixing with the original mixture to promote partial mixing thereof; and circumferentially spaced dilution apertures for admitting dilution air into the combustor to promote partial mixing with the original mixture. The first and second apertures are axially located in a secondary combustion zone of the combustor and upstream of the turbine vanes to induce partial mixing of the dilution air with the hot gases for generating a preselected circumferential temperature gradient in the hot gas for providing a flow of hot gas at a relatively higher temperature through the gaps and a flow of hot gas at relatively lower temperature upon the turbine vanes.
- Assignee:
- General Electric Co., Lynn, MA
- Patent Number(s):
- US 4733538
- OSTI ID:
- 5106602
- Resource Relation:
- Patent File Date: Filed date 9 Feb 1981
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
GAS TURBINE ENGINES
COMBUSTORS
FUEL SYSTEMS
APERTURES
DILUTION
FINS
FUEL-AIR RATIO
GAS FLOW
HEAT TRANSFER
JACKETS
TEMPERATURE CONTROL
CONTROL
ENERGY TRANSFER
ENGINES
FLUID FLOW
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
OPENINGS
330103* - Internal Combustion Engines- Turbine