公开(公告)号：US10823194B2

公开(公告)日：2020-11-03

申请号：US14556315

申请日：2014-12-01

Applicant: General Electric Company

Inventor： Giridhar Jothiprasad ,  Ramakrishna Venkata Mallina ,  John David Stampfli ,  Rudolf Konrad Selmeier ,  Davide Giacché

IPC: F04D29/40 ,  F01D5/14 ,  F01D25/24 ,  F04D29/52 ,  F04D29/68

Abstract: A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.

公开(公告)号：US10260417B2

公开(公告)日：2019-04-16

申请号：US14977854

申请日：2015-12-22

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Davide Giacché ,  Kishore Ramakrishnan

IPC: F02C7/04 ,  B64C7/02 ,  B64D27/12 ,  B64D27/14

Abstract: A turboprop assembly includes a nacelle with a main nacelle body and a nacelle extension coupled to the main nacelle body. The nacelle extension has a wall that defines an air intake port. The air intake port has a non-circular, non-rectangular, and non-oval shaped perimeter extending in two of three dimensions.

公开(公告)号：US10047620B2

公开(公告)日：2018-08-14

申请号：US14572119

申请日：2014-12-16

Applicant: General Electric Company

Inventor： Davide Giacché ,  John David Stampfli ,  Ramakrishna Venkata Mallina ,  Vittorio Michelassi ,  Giridhar Jothiprasad ,  Ajay Keshava Rao ,  Rudolf Konrad Selmeier ,  Sungho Yoon ,  Ivan Malcevic

IPC: F01D11/00 ,  F04D29/52 ,  F04D29/68 ,  F04D27/02

Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.