公开(公告)号：US10816014B2

公开(公告)日：2020-10-27

申请号：US16044704

申请日：2018-07-25

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shakeel Nasir ,  John Schugardt ,  Mahmoud Mansour ,  Richard Bonvouloir

IPC: F04D29/70 ,  F02C3/08 ,  F04D29/44 ,  B01D45/12 ,  F01D25/32 ,  B01D45/04 ,  F01D1/14 ,  F02C7/052

Abstract: A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.

公开(公告)号：US20180135516A1

公开(公告)日：2018-05-17

申请号：US15352839

申请日：2016-11-16

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shakeel Nasir ,  Yogendra Yogi Sheoran ,  John Schugardt ,  Daniel Aukland ,  Mahmoud Mansour ,  Cristopher Frost ,  Matt Greenman

IPC: F02C7/052

CPC classification number: F02C7/052 ,  F02C3/04 ,  F02C7/00 ,  F04D29/444 ,  F04D29/701 ,  F05D2250/52 ,  F05D2260/607 ,  Y02T50/675

Abstract: A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not operation, but does not occur continuously during engine operation.

公开(公告)号：US20170211586A1

公开(公告)日：2017-07-27

申请号：US15006551

申请日：2016-01-26

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Raymond Gage ,  Bruce David Reynolds ,  Jeffrey D. Harrison ,  Michael Todd Barton ,  Mahmoud Mansour ,  Kent L. Kime

IPC: F04D29/42 ,  F04D29/58 ,  F04D29/28

CPC classification number: F04D29/4206 ,  F02C3/08 ,  F02C6/08 ,  F04D29/284 ,  F04D29/444 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/30 ,  F05D2260/20 ,  Y02T50/671

Abstract: Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.