发明名称 |
Direct heating surface combustor |
摘要 |
A direct heating surface combustor is provided that utilizes a non-adiabatic flame to provide a low-emission combustion for gas turbines. A fuel-air mixture is directed through a porous wall, the other side of which serves as a combustion surface. A radiant heat sink disposed adjacent to and spaced from the combustion surface controls the combustor flame temperature in order to prevent the formation of oxides of nitrogen. A secondary air flow cools the heat sink. Additionally, up to 100% of secondary air flow is mixed with the combustion products at the direct heating surface combustor to dilute such products thereby reducing exit temperature. However, if less than 100% secondary air is mixed at the combustor, the remainder may be added to the combustion products further downstream.
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申请公布号 |
US4087962(A) |
申请公布日期 |
1978.05.09 |
申请号 |
US19760708660 |
申请日期 |
1976.07.26 |
申请人 |
THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION |
发明人 |
BEREMAND, DONALD G.;SHURE, LLOYD I.;MROZ, THADDEUS S. |
分类号 |
F23D14/14;F23D17/00;F23R3/04;F23R3/28;(IPC1-7):F02C7/22;F23D13/14 |
主分类号 |
F23D14/14 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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