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1. 发明申请

US20070028595A1 High pressure gas turbine engine having reduced emissions 审中-公开
标题翻译：具有减少排放的高压燃气涡轮发动机
公开(公告)号：US20070028595A1
公开(公告)日：2007-02-08
申请号：US11188483
申请日：2005-07-25
申请人： Hukam Mongia , George Hsiao , Shui-Chi Li , Shih-Yang Hsieh , Alfred Mancini , David Burrus , Marie McMasters , Duane Thomsen
发明人： Hukam Mongia , George Hsiao , Shui-Chi Li , Shih-Yang Hsieh , Alfred Mancini , David Burrus , Marie McMasters , Duane Thomsen
IPC分类号： F02K3/04 , F23R3/14
CPC分类号： F02K3/04 , F05D2270/082 , F23R3/06 , F23R3/14 , F23R3/286 , F23R3/343 , Y02T50/675 , Y02T50/677
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including a fan section at a forward end of the gas turbine engine for producing a first compressed air flow; a first compressor positioned downstream of the fan section and in flow communication with at least a portion of the first compressed air flow, wherein the first compressor produces a second compressed air flow having a designated pressure; a combustor positioned downstream of the first compressor and in flow communication with second compressed air flow, wherein the combustor produces combustion products from a mixture of fuel and air; a first turbine positioned downstream of the combustor and in flow communication with combustion products, wherein the first turbine powers the first compressor by means of a first rotatable drive shaft connected therebetween; and, a second turbine positioned downstream of the first turbine and in flow communication with the combustion products exiting the first turbine, wherein the second turbine powers the fan section by means of a second drive shaft connected therebetween. The gas turbine engine produces no more than a predetermined amount of emissions during an operating cycle.
摘要翻译：一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括在所述燃气涡轮发动机的前端处的风扇部分，用于产生第一压缩空气流; 第一压缩机，其位于所述风扇部分的下游并且与所述第一压缩空气流的至少一部分流动连通，其中所述第一压缩机产生具有指定压力的第二压缩空气流; 位于所述第一压缩机下游并与所述第二压缩空气流流动连通的燃烧器，其中所述燃烧器从燃料和空气的混合物产生燃烧产物; 位于燃烧器下游并与燃烧产物流动的第一涡轮机，其中第一涡轮机通过连接在其间的第一可旋转驱动轴来驱动第一压缩机; 以及位于第一涡轮机下游并与离开第一涡轮机的燃烧产物流动连通的第二涡轮机，其中第二涡轮机通过连接在其间的第二驱动轴为风扇部分供电。燃气涡轮发动机在操作循环期间产生不超过预定量的排放。

2. 发明申请

US20110126909A1 ROTARY UNION WITH SELECTIVELY CONTROLLED SEAL 有权
标题翻译：旋转联盟与选择性控制密封
公开(公告)号：US20110126909A1
公开(公告)日：2011-06-02
申请号：US12628642
申请日：2009-12-01
申请人： David Burrus , Graig Aaron LaCroix
发明人： David Burrus , Graig Aaron LaCroix
IPC分类号： G05D16/06 , F16L17/06
CPC分类号： F16L27/082 , Y10T137/0318 , Y10T137/86268 , Y10T137/87917
摘要： A rotary union includes a non-rotating machine component having a receiving counterbore, a media channel opening, and a control channel. A housing is positioned within the receiving counterbore and has a bore and a control chamber in fluid communication with the control channel. A non-rotating seal member is slidably and sealingly disposed within the bore in the housing and has a media channel in fluid communication with the media channel opening and the receiving counterbore. The non-rotating seal member can be selectively extended or retracted within the bore of the housing, such that selective engagement of a face seal is accomplished under different operating conditions of the rotary union.
摘要翻译：旋转联接器包括具有接收沉头孔，介质通道开口和控制通道的非旋转机器部件。壳体定位在接收沉孔内，并且具有与控制通道流体连通的孔和控制室。非旋转密封件可滑动地且密封地设置在壳体内的孔内，并且具有与介质通道开口和接收沉孔流体连通的介质通道。非旋转密封构件可以选择性地在壳体的孔内延伸或缩回，使得面密封件的选择性接合在旋转接头的不同操作条件下完成。

3. 发明授权

US08453675B2 Rotary union with selectively controlled seal 有权
标题翻译：旋转联合，带有选择性控制密封
公开(公告)号：US08453675B2
公开(公告)日：2013-06-04
申请号：US12628642
申请日：2009-12-01
申请人： David Burrus , Graig Aaron LaCroix
发明人： David Burrus , Graig Aaron LaCroix
IPC分类号： F16L33/16
CPC分类号： F16L27/082 , Y10T137/0318 , Y10T137/86268 , Y10T137/87917
摘要： A rotary union includes a non-rotating machine component having a receiving counterbore, a media channel opening, and a control channel. A housing is positioned within the receiving counterbore and has a bore and a control chamber in fluid communication with the control channel. A non-rotating seal member is slidably and sealingly disposed within the bore in the housing and has a media channel in fluid communication with the media channel opening and the receiving counterbore. The non-rotating seal member can be selectively extended or retracted within the bore of the housing, such that selective engagement of a face seal is accomplished under different operating conditions of the rotary union.
摘要翻译：旋转联接器包括具有接收沉头孔，介质通道开口和控制通道的非旋转机器部件。壳体定位在接收沉孔内，并且具有与控制通道流体连通的孔和控制室。非旋转密封件可滑动地且密封地设置在壳体内的孔内，并且具有与介质通道开口和接收沉孔流体连通的介质通道。非旋转密封构件可以选择性地在壳体的孔内延伸或缩回，使得面密封件的选择性接合在旋转接头的不同操作条件下完成。

4. 发明申请

US20050034458A1 GAS TURBINE ENGINE COMBUSTOR CAN WITH TRAPPED VORTEX CAVITY 有权
标题翻译：燃气涡轮发动机可以搭配VORTEX CAVITY
公开(公告)号：US20050034458A1
公开(公告)日：2005-02-17
申请号：US10762993
申请日：2004-01-22
申请人： David Burrus , Narendra Joshi , Joel Haynes , Alan Feitelberg
发明人： David Burrus , Narendra Joshi , Joel Haynes , Alan Feitelberg
IPC分类号： F23R3/18 , F02C7/18 , F23R3/06 , F23R3/28 , F23R3/32 , F23R3/34 , F23R3/58 , F23R3/42
CPC分类号： F23R3/346 , F23C2900/07001 , F23D2900/14004 , F23R3/283 , F23R3/286 , F23R3/58 , F23R2900/00015
摘要： A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.
摘要翻译：在预混合器下游的燃气涡轮发动机燃烧器具有预混合器流动路径，并且横跨预混合器流动路径设置周向间隔开的涡流叶片。主燃料喷射器定位成将燃料喷射到预混合器流路中。由环形燃烧器衬套围绕的燃烧室，其设置成与预混合器供应流动连通。位于燃烧器衬套的上游端的环形捕获双涡流腔限定在环形后壁，环形前壁和形成在其间的圆形径向外壁。在空腔的径向内端处的空腔开口与径向外壁间隔开。空气注入第一孔穿过前壁设置，空气注入第二孔穿过后壁。燃料喷射孔通过前壁和后壁中的至少一个设置。

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