公开(公告)号：US09938831B2

公开(公告)日：2018-04-10

申请号：US13283689

申请日：2011-10-28

Applicant: Gabriel L. Suciu ,  Stephen P. Muron ,  Ioannis Alvanos ,  Christopher M. Dye ,  Brian D. Merry ,  Arthur M. Salve ,  James W. Norris

Inventor： Gabriel L. Suciu ,  Stephen P. Muron ,  Ioannis Alvanos ,  Christopher M. Dye ,  Brian D. Merry ,  Arthur M. Salve ,  James W. Norris

IPC: F01D5/06 ,  F01D5/02

CPC classification number: F01D5/026 ,  F01D5/06 ,  F01D5/066

Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.

公开(公告)号：US09157325B2

公开(公告)日：2015-10-13

申请号：US13405502

申请日：2012-02-27

Applicant: Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

Inventor： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

IPC: F02C6/08 ,  F01D5/08 ,  F02C7/06 ,  F02C7/18

CPC classification number: F01D5/081 ,  F02C6/08 ,  F02C7/06 ,  F02C7/185

Abstract: A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine.

Abstract translation: 燃气涡轮发动机包括具有第一热交换器，第一通道，第二通道和第三通道的缓冲冷却系统。 第一热交换器与放气气流交换热量以提供调节气流。 第一通道将调节气流的第一部分与燃气涡轮发动机的高压压缩机连通，第二通道将调节气流的第二部分连通到燃气涡轮发动机的高压涡轮机，并且第三通道 调节气流的第三部分到燃气涡轮发动机的低压涡轮机。

公开(公告)号：US08770931B2

公开(公告)日：2014-07-08

申请号：US13116144

申请日：2011-05-26

Applicant: Ioannis Alvanos ,  Gabriel L. Suciu

Inventor： Ioannis Alvanos ,  Gabriel L. Suciu

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D5/284 ,  C04B37/001 ,  C04B2237/38 ,  C04B2237/86 ,  F01D5/282 ,  F01D9/041 ,  F01D11/001 ,  F01D25/246 ,  F05D2300/6033 ,  Y10T29/49321 ,  Y10T29/49323

Abstract: A vane structure for a gas turbine engine includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a metal alloy inner ring.

Abstract translation: 用于燃气涡轮发动机的叶片结构包括集成在CMC外环和金属合金内圈之间的多个CMC翼型部分。

公开(公告)号：US08511986B2

公开(公告)日：2013-08-20

申请号：US12001130

申请日：2007-12-10

Applicant: Ioannis Alvanos ,  Gabriel L. Suciu

Inventor： Ioannis Alvanos ,  Gabriel L. Suciu

IPC: F04D29/04

CPC classification number: F02C7/06 ,  F01D25/16 ,  F05D2220/321 ,  Y02T50/671

Abstract: A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft.

公开(公告)号：US20130108466A1

公开(公告)日：2013-05-02

申请号：US13283710

申请日：2011-10-28

Applicant: Gabriel L. Suciu ,  Stephen P. Muron ,  Christopher M. Dye ,  Ioannis Alvanos ,  Brian D. Merry

Inventor： Gabriel L. Suciu ,  Stephen P. Muron ,  Christopher M. Dye ,  Ioannis Alvanos ,  Brian D. Merry

IPC: F01D5/14 ,  B21D53/00 ,  F01D5/00

CPC classification number: F01D5/02 ,  F01D5/022 ,  F01D5/025 ,  F01D5/027 ,  F01D5/066 ,  F01D5/14 ,  F01D5/147 ,  F01D11/006 ,  F05D2240/20 ,  F05D2260/15 ,  Y10T29/49316 ,  Y10T29/4932

Abstract: A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.

Abstract translation: 用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环，转子环限定限定第一厚度的前周向凸缘和限定第二厚度的后周向凸缘，第一厚度不同于第二厚度 。 多个核心气体路径密封件，其从转子环延伸，与斜坡界面相对。

公开(公告)号：US20130108445A1

公开(公告)日：2013-05-02

申请号：US13283689

申请日：2011-10-28

Applicant: Gabriel L. Suciu ,  Stephen P. Muron ,  Ioannis Alvanos ,  Christopher M. Dye ,  Brian D. Merry ,  Arthur M. Salve ,  James W. Norris

Inventor： Gabriel L. Suciu ,  Stephen P. Muron ,  Ioannis Alvanos ,  Christopher M. Dye ,  Brian D. Merry ,  Arthur M. Salve ,  James W. Norris

IPC: F01D5/08 ,  F01D5/12 ,  F01D5/04

CPC classification number: F01D5/026 ,  F01D5/06 ,  F01D5/066

Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.

Abstract translation: 用于燃气涡轮发动机的转子包括从转子盘延伸的多个叶片，所述多个叶片中的每一个叶片在接合处从转子盘延伸，所述界面沿辐条限定。

公开(公告)号：US20130000324A1

公开(公告)日：2013-01-03

申请号：US13172316

申请日：2011-06-29

Applicant: Ioannis Alvanos ,  Gabriel L. Suciu

Inventor： Ioannis Alvanos ,  Gabriel L. Suciu

IPC: F02C3/04

CPC classification number: F01D9/044 ,  F01D9/041 ,  F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F05D2230/53 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.

Abstract translation: 燃气涡轮发动机包括压缩机，燃烧器部分和涡轮机。 涡轮机包括由陶瓷基体复合材料组成的集成壳体/定子段。

公开(公告)号：US20120321453A1

公开(公告)日：2012-12-20

申请号：US13164234

申请日：2011-06-20

Applicant: Ioannis Alvanos

Inventor： Ioannis Alvanos

IPC: F01D5/08 ,  B21K25/00

CPC classification number: F01D5/081 ,  F02C7/18 ,  F05D2260/30 ,  Y02T50/676 ,  Y10T29/49327

Abstract: A high pressure turbine includes a stator, a rotor, a tangential on-board injector, and a heat shield. The rotor is located downstream of the stator and the tangential on-board injector directs cooling air to the rotor. The heat shield is retained by abutment with the stator and the tangential on-board injector.

Abstract translation: 高压涡轮机包括定子，转子，切向的车载喷射器和隔热罩。 转子位于定子的下游，切向的车载喷射器将冷却空气引导到转子。 隔热板通过与定子和切向机载喷射器的邻接保持。

公开(公告)号：US20120301306A1

公开(公告)日：2012-11-29

申请号：US13116199

申请日：2011-05-26

Applicant: Ioannis Alvanos ,  Gabriel L. Suciu ,  Christopher M. Dye ,  Glenn Levasseur

Inventor： Ioannis Alvanos ,  Gabriel L. Suciu ,  Christopher M. Dye ,  Glenn Levasseur

IPC: F01D5/30

CPC classification number: F01D5/3046 ,  F01D5/225 ,  F01D5/282 ,  F01D5/284 ,  F05D2300/6033

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor hub defined about an axis of rotation, the rotor hub includes a blade mount section with a first radial flange having a multiple of first apertures and a second radial flange with a multiple of second apertures.

Abstract translation: 用于燃气涡轮发动机的转子盘组件包括围绕旋转轴限定的转子毂，转子毂包括具有第一径向凸缘的叶片安装部分，第一径向凸缘具有多个第一孔，第二径向凸缘具有多个第二孔 。

公开(公告)号：US20120297791A1

公开(公告)日：2012-11-29

申请号：US13116116

申请日：2011-05-26

Applicant: Gabriel L. Suciu ,  Ioannis Alvanos ,  Brian D. Merry

Inventor： Gabriel L. Suciu ,  Ioannis Alvanos ,  Brian D. Merry

IPC: F01N13/00 ,  F02K1/00 ,  B23P15/04 ,  F02C3/00

CPC classification number: F02C7/20 ,  F01D9/041 ,  F01D25/30 ,  F02K1/04 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/4932

Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.

Abstract translation: 用于燃气涡轮发动机的涡轮机排气箱包括在CMC核心机舱后部和CMC尾锥之间的多个CMC涡轮机排气外壳支柱。