公开(公告)号：US11808175B2

公开(公告)日：2023-11-07

申请号：US17109484

申请日：2020-12-02

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Constantinos Vogiatzis ,  Yoseph Gebre-Giorgis

IPC: F01D9/04 ,  F01D5/16 ,  F01D5/14

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/16 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/125 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/711 ,  F05D2260/941

Abstract: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions include an airfoil tip, and an airfoil root opposite the airfoil tip in a spanwise direction. The GTE airfoil has a first, second and third locally-thickened region, with the first locally-thickened region defined at the airfoil root. A maximum thickness of each chord between the airfoil root and the airfoil tip transitions toward the leading edge between the first locally-thickened region and the second locally-thickened region, and the third locally-thickened region extends in the spanwise direction. A chord line that extends through the third locally-thickened region contains a first local thickness maxima and a second local thickness maxima interspersed with at least two local thickness minima, and the first local thickness maxima is defined by the third locally-thickened region and is greater than the second local thickness maxima.

公开(公告)号：US10907648B2

公开(公告)日：2021-02-02

申请号：US15671407

申请日：2017-08-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Constantinos Vogiatzis

IPC: F04D29/38 ,  F04D29/32

Abstract: A fan blade for a gas turbine engine includes an airfoil that has a first chord line that extends from a leading edge to a trailing edge. The first chord line is at 0% at the leading edge and at 100% at the trailing edge. The airfoil has a first local maximum thickness defined between about 85% of a span to a tip, a second local maximum thickness defined between about 40% to about 85% of the span and a third local maximum thickness defined between a root to about 40% of the span. The second local maximum thickness is positioned at about 10% to about 30% of the first chord line so as to be offset from the first local maximum thickness in the chordwise direction toward the leading edge. Each of the first, second and third local maximum thicknesses are different.

公开(公告)号：US10895161B2

公开(公告)日：2021-01-19

申请号：US15338026

申请日：2016-10-28

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Constantinos Vogiatzis ,  Yoseph Gebre-Giorgis

IPC: F01D9/04 ,  F01D5/16 ,  F01D5/14

Abstract: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions are provided. In one embodiment, the GTE airfoil includes an airfoil tip, an airfoil root opposite the airfoil tip in a spanwise direction, and first and second airfoil halves extending between the airfoil tip and the airfoil root. The first airfoil half has a first multimodal thickness distribution, as taken in a cross-section plane extending in the spanwise direction and in a thickness direction substantially perpendicular to the spanwise direction. The first multimodal thickness distribution may be defined by multiple locally-thickened airfoil regions, which are interspersed with multiple locally-thinned airfoil regions. The second airfoil half may or may not have a multimodal thickness distribution. By imparting at least one airfoil half with such a multimodal thickness distribution, targeted mechanical properties of the GTE airfoil may be enhanced with relatively little impact on aerodynamic performance.

公开(公告)号：US20180119706A1

公开(公告)日：2018-05-03

申请号：US15671407

申请日：2017-08-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Constantinos Vogiatzis

IPC: F04D29/38 ,  F04D29/32

CPC classification number: F04D29/384 ,  F04D29/324 ,  F04D29/325

Abstract: A fan blade for a gas turbine engine includes an airfoil that has a first chord line that extends from a leading edge to a trailing edge. The first chord line is at 0% at the leading edge and at 100% at the trailing edge. The airfoil has a first local maximum thickness defined between about 85% of a span to a tip, a second local maximum thickness defined between about 40% to about 85% of the span and a third local maximum thickness defined between a root to about 40% of the span. The second local maximum thickness is positioned at about 10% to about 30% of the first chord line so as to be offset from the first local maximum thickness in the chordwise direction toward the leading edge. Each of the first, second and third local maximum thicknesses are different.

公开(公告)号：US11280199B2

公开(公告)日：2022-03-22

申请号：US16198260

申请日：2018-11-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Michael R. McNamee ,  Nick Nolcheff ,  Yoseph Gebre-Giorgis ,  John A. Gunaraj ,  Jeffrey Hayes ,  Constantinos Vogiatzis

IPC: F01D5/14 ,  F01D5/02

Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from a leading edge to a trailing edge. The airfoil has a location of local maximum thickness defined as a ratio of a first arc distance along the mean camber line between the leading edge and a position of the local maximum thickness to a total arc distance along the mean camber line from the leading edge to the trailing edge. A value of the ratio increases from the root to a first position value, decreases from the first position value to a second position value and increases from the second position value to the tip. The first position value is at a spanwise location within 20% to 50% of the span.

公开(公告)号：US20210102472A1

公开(公告)日：2021-04-08

申请号：US17109484

申请日：2020-12-02

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Constantinos Vogiatzis ,  Yoseph Gebre-Giorgis

IPC: F01D9/04 ,  F01D5/16 ,  F01D5/14

Abstract: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions include an airfoil tip, and an airfoil root opposite the airfoil tip in a spanwise direction. The GTE airfoil has a first, second and third locally-thickened region, with the first locally-thickened region defined at the airfoil root. A maximum thickness of each chord between the airfoil root and the airfoil tip transitions toward the leading edge between the first locally-thickened region and the second locally-thickened region, and the third locally-thickened region extends in the spanwise direction. A chord line that extends through the third locally-thickened region contains a first local thickness maxima and a second local thickness maxima interspersed with at least two local thickness minima, and the first local thickness maxima is defined by the third locally-thickened region and is greater than the second local thickness maxima.

公开(公告)号：US20200157941A1

公开(公告)日：2020-05-21

申请号：US16198260

申请日：2018-11-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Michael R. McNamee ,  Nick Nolcheff ,  Yoseph Gebre-Giorgis ,  John A. Gunaraj ,  Jeffrey Hayes ,  Constantinos Vogiatzis

IPC: F01D5/14 ,  F01D5/02

Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from a leading edge to a trailing edge. The airfoil has a location of local maximum thickness defined as a ratio of a first arc distance along the mean camber line between the leading edge and a position of the local maximum thickness to a total arc distance along the mean camber line from the leading edge to the trailing edge. A value of the ratio increases from the root to a first position value, decreases from the first position value to a second position value and increases from the second position value to the tip. The first position value is at a spanwise location within 20% to 50% of the span.

公开(公告)号：US20180119555A1

公开(公告)日：2018-05-03

申请号：US15338026

申请日：2016-10-28

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Constantinos Vogiatzis ,  Yoseph Gebre-Giorgis

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/16 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/125 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/711 ,  F05D2260/941

Abstract: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions are provided. In one embodiment, the GTE airfoil includes an airfoil tip, an airfoil root opposite the airfoil tip in a spanwise direction, and first and second airfoil halves extending between the airfoil tip and the airfoil root. The first airfoil half has a first multimodal thickness distribution, as taken in a cross-section plane extending in the spanwise direction and in a thickness direction substantially perpendicular to the spanwise direction. The first multimodal thickness distribution may be defined by multiple locally-thickened airfoil regions, which are interspersed with multiple locally-thinned airfoil regions. The second airfoil half may or may not have a multimodal thickness distribution. By imparting at least one airfoil half with such a multimodal thickness distribution, targeted mechanical properties of the GTE airfoil may be enhanced with relatively little impact on aerodynamic performance.