公开(公告)号：US20120031098A1

公开(公告)日：2012-02-09

申请号：US13196968

申请日：2011-08-03

Applicant: Leonid Ginessin ,  Borys Shershnyov ,  Almaz Valeev

Inventor： Leonid Ginessin ,  Borys Shershnyov ,  Almaz Valeev

IPC: F02C7/12

CPC classification number: F23R3/283 ,  F23C2900/07001 ,  F23D2214/00 ,  F23R3/14

Abstract: A fuel nozzle for turbine engine includes a cooling shroud located at the downstream end of the fuel nozzle to help cool the downstream end of the fuel nozzle. The cooling shroud surrounds the exterior circumference of the downstream end of the fuel nozzle. A flow of air is admitted into the cooling shroud and the flow of air travels in the downstream direction through a first passageway which covers the exterior of the fuel nozzle. The cooling air flow then turns 180° and travels in the upstream direction through a second passageway which is located concentrically outside the first passageway. The airflow then leaves the upstream end of the cooling shroud and enters the interior of the fuel nozzle.

Abstract translation: 用于涡轮发动机的燃料喷嘴包括位于燃料喷嘴的下游端的冷却罩，以帮助冷却燃料喷嘴的下游端。 冷却罩围绕燃料喷嘴的下游端的外周。 空气流进入冷却护罩，空气流沿下游方向通过覆盖燃料喷嘴外部的第一通道。 然后，冷却空气流转动180°并沿上游方向通过位于第一通道同心位置的第二通道。 气流然后离开冷却罩的上游端并进入燃料喷嘴的内部。

公开(公告)号：US20110239652A1

公开(公告)日：2011-10-06

申请号：US12754813

申请日：2010-04-06

Applicant: Kevin Weston McMahan ,  Almaz Valeev ,  Chunyang Wu

Inventor： Kevin Weston McMahan ,  Almaz Valeev ,  Chunyang Wu

IPC: F02C7/22

CPC classification number: F23R3/286 ,  F23R3/34

Abstract: A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.

Abstract translation: 提供了燃烧器部分，并且包括分段的环形歧管，其在燃料喷嘴支撑件的上游位于通道的部分中，氧化剂通过该部分流动，歧管的每个部分基本上轴向对齐并且包括主体以容纳内部形成的燃料 以限定喷射孔，燃料通过该喷射孔注入到燃料喷嘴支撑件上游的氧化剂流过的通道中。

公开(公告)号：US20110173984A1

公开(公告)日：2011-07-21

申请号：US12917561

申请日：2010-11-02

Applicant: Almaz Valeev ,  Leonid Ginessin ,  Sergey Anatolievich Meshkov

Inventor： Almaz Valeev ,  Leonid Ginessin ,  Sergey Anatolievich Meshkov

IPC: F01D25/24

CPC classification number: F01D9/023 ,  F01D17/141 ,  F02C9/18 ,  F05D2250/411

Abstract: An air bypass band assembly includes a transition piece of a gas turbine, the transition piece having at least one opening therein to allow a flow of air to pass through the at least one opening. The air bypass band assembly also includes a band that is movable between at least two positions, a first one of the at least two positions being a closed position where the at least one opening is closed to prevent the flow of air from flowing through the at least one opening, a second one of the at least two positions being an open where the at least one opening is opened to allow the flow of air to flow through the at least one opening. The air bypass band assembly further includes a mechanism that moves the band between the at least two positions.

Abstract translation: 空气旁路带组件包括燃气轮机的过渡件，所述过渡件在其中具有至少一个开口，以允许空气流通过所述至少一个开口。 空气旁路带组件还包括能够在至少两个位置之间移动的带，所述至少两个位置中的第一位置是闭合位置，其中所述至少一个开口被封闭，以防止空气流通过 至少一个开口，所述至少两个位置中的第二位置是开放的，其中所述至少一个开口被打开以允许空气流通过所述至少一个开口。 空气旁通带组件还包括使带在至少两个位置之间移动的机构。