| 摘要 |
<p>A method of combustor cycle air flow adjustment for a gas turbine engine to solve the problem of a higher flame temperature in the combustor, affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors emission levels are significantly dependent on the primary combustion zone flame temperature. flame temperature in a primary combustion zone of a combustor can be maintained substantially the same whether the gas turbine engine is used to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine by changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for a combustion and an air mass flow for cooling. In an embodiment of the present invention changing the number and size of perforations in an impingement cooling skin serves duel purposes both as a cooling device for cooling the combustor wall and as a valve means for combustor cycle air flow adjustment.</p> |
