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公开(公告)号：US5487274A
公开(公告)日：1996-01-30
申请号：US225489
申请日：1994-04-08
CPC分类号： F23R3/16 , F23D14/02 , F23D2210/00 , F23R2900/00014
摘要： Combustion-induced unsteady oscillations referred to as screech are suppressed in gas turbine combustors by a plurality (preferably two to six) of screech suppression members disposed in the premixers of the combustors. The screech suppression members are attached to the centerbody of the premixer and extend radially outward, nearly into contact with the inner surface of the premixer tube. The screech suppression members are uniformly spaced about the centerbody and are axially positioned at or near the end of the centerbody which is closest to the main combustion chamber. Alternatively, each screech suppression member can be attached to the inner surface of the premixer tube and extend radially inward nearly into contact with the centerbody. Possible shapes of the screech suppression members include a thick block, a thin rectangular plate, a triangular plate, a V-shaped member, and a cylindrical bar.
摘要翻译： 被称为尖叫声的燃烧引起的非稳态振荡在燃气轮机燃烧器中通过设置在燃烧器的预混合器中的多个（优选两到六个）尖叫抑制构件来抑制。 尖叫抑制构件附接到预混合器的中心体并且径向向外延伸，几乎与预混合管的内表面接触。 尖叫声抑制构件围绕中心体均匀间隔开并且轴向定位在最靠近主燃烧室的中心体的端部处或附近。 或者，每个尖叫抑制构件可以附接到预混合管的内表面并且径向向内延伸地与中心体接触。 尖叫抑制构件的可能形状包括厚块，薄矩形板，三角形板，V形构件和圆柱形杆。
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公开(公告)号：US5253474A
公开(公告)日：1993-10-19
申请号：US753139
申请日：1991-08-30
摘要： A supersonic combustion ramjet having a supersonic combustor. The supersonic combustor has a backward-facing step formed in a wall thereof and a forward-facing ramp formed in the wall downstream from the step. Hydrogen fuel is injected into the air flow by axially-directed fuel injectors disposed in the step and/or normally-directed fuel injectors disposed in the ramp. The ramp is inclined toward the center of the combustor so that fuel from the fuel injectors is turned into the main flow. The ensures rapid mixing which enables combustion to be completed within a distance on the order of one foot.
摘要翻译： 具有超音速燃烧器的超音速燃烧冲压式喷气式发动机。 超音速燃烧器具有在其壁中形成的向后的台阶和形成在台阶下游的壁中的前向斜面。 通过设置在设置在斜坡中的台阶和/或正常定向的燃料喷射器中的轴向定向的燃料喷射器将氢燃料喷射到空气流中。 斜坡朝向燃烧器的中心倾斜，使得来自燃料喷射器的燃料变成主流。 确保快速混合，使燃烧在一英尺数量级的距离内完成。
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公开(公告)号：US6141967A
公开(公告)日：2000-11-07
申请号：US5343
申请日：1998-01-09
申请人： Paul R. Angel , James M. Caldwell , Narendra D. Joshi , Steven Marakovits , Kelley A. Foresman , Steven G. Goebel , Richard E. Warren, Jr.
发明人： Paul R. Angel , James M. Caldwell , Narendra D. Joshi , Steven Marakovits , Kelley A. Foresman , Steven G. Goebel , Richard E. Warren, Jr.
摘要： An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, including: a linear mixing duct having a circular cross-section defined by a wall; a centerbody located along a central axis of the mixing duct and extending substantially the full length of the mixing duct, the centerbody having a plurality of orifices therein to inject fuel into the mixing duct with an axial velocity component; a fuel supply in flow communication with the centerbody orifices; an outer annular swirler located adjacent an upstream end of the mixing duct and including a plurality of circumferentially spaced vanes oriented so as to swirl air flowing therethrough in a first direction; an inner annular swirler located adjacent the mixing duct upstream end and including a plurality of circumferentially spaced vanes, the vanes having an outer radial portion having a leading edge and a trailing edge oriented so as to swirl air flowing therethrough in a second direction opposite the first swirl direction by the outer annular swirler vanes and an inner radial portion with a leading edge and a trailing edge oriented so as to provide a boundary layer of air substantially along the centerbody; and, a hub separating the inner and outer annular swirlers to permit independent rotation of an air stream therethrough. The outer annular swirler may also include vanes having an inner radial portion with a leading edge and a trailing edge oriented so as to swirl the air flow therethrough and an outer radial portion having a leading edge and a trailing edge oriented so as to provide a boundary layer of air substantially along the mixing duct wall. High pressure air is injected from a compressor into the mixing duct through the inner and outer annular swirlers and fuel is injected into the mixing duct so that the high pressure air and the fuel is uniformly mixed therein, whereby minimal formation of pollutants is produced when the fuel/air mixture is exhausted out the downstream end of the mixing duct into a combustor and ignited.
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