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公开(公告)号：US20160369816A1
公开(公告)日：2016-12-22
申请号：US15252331
申请日：2016-08-31
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Matthew P. Forcier , Brian J. Schuler
CPC classification number: F04D29/324 , F01D5/082 , F01D5/146 , F01D11/001 , F04D29/584 , F05D2240/126 , F05D2240/129 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine has a compressor section with a downstream most blade stage and a downstream vane row positioned downstream of the downstream most blade stage. The downstream most blade stage includes a plurality of blade pairs with the majority of blade pairs being circumferentially spaced apart from others of the blade pairs, each the blade pair being operatively connected to a rotor disk disposed radially inward from the blade pairs with each blade pair including a forward blade and an aft blade. The aft blades are configured to further condition airflow with respect to the forward blade. A tangential onboard injector (TOBI) is positioned radially inwardly of the downstream vane row.
Abstract translation: 燃气涡轮发动机具有压缩机部分，其具有下游最多的叶片级和位于下游最大叶片级的下游叶片排。 下游的大多数叶片级包括多个叶片对，其中大多数叶片对与叶片对中的其它叶片对沿周向间隔开，每个叶片对可操作地连接到从每个叶片对的叶片对径向向内设置的转子盘 包括前刀片和后刀片。 后叶片构造成进一步调节相对于前叶片的气流。 切向机载喷油器（TOBI）位于下游叶片排的径向内侧。
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公开(公告)号：US20150218955A1
公开(公告)日：2015-08-06
申请号：US14422368
申请日：2013-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew E. Bintz , Peter T. Schutte , Brian J. Schuler , Anthony R. Bifulco
CPC classification number: F01D5/288 , F01D5/14 , F01D5/141 , F01D5/20 , F01D9/04 , F01D11/122 , F05D2240/125 , F05D2240/307 , Y02T50/673
Abstract: A cantilevered airfoil includes, among other things, an airfoil having a body section and a tip, the body section extending in a first direction that is angled relative to a radial direction, the tip of the airfoil angled radially in a second direction relative to the body section.
Abstract translation: 悬臂式翼型件尤其包括具有主体部分和尖端的翼型件，主体部分沿相对于径向成角度的第一方向延伸，翼型件的尖端相对于第二方向沿第二方向径向地成角度 身体部位。
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