公开(公告)号：US20250012233A1

公开(公告)日：2025-01-09

申请号：US18452748

申请日：2023-08-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Hasham Chougule ,  Shripad Thakur ,  Kaustubh Mohta ,  John Gunaraj ,  David Hanson ,  Michael Barton ,  Mahmoud Mansour

IPC: F02K1/40 ,  F02C3/04

Abstract: Gas turbine engines are provided that include an annular splitter nose structure configured to impinge an accelerated air stream within the gas turbine engine and separate the accelerated air stream into a primary air stream directed into a core duct and a secondary air stream directed into a bypass duct. The splitter nose structure may include a leading edge that is pitched radially outward relative to a rotational axis of the gas turbine engine at a pitch angle of between about 0.5 and 20 degrees. The splitter nose structure may include an irregular cross-sectional shape.

公开(公告)号：US20210381380A1

公开(公告)日：2021-12-09

申请号：US16892145

申请日：2020-06-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Repp ,  Bruce Reynolds ,  John Gunaraj

IPC: F01D5/02 ,  F02C7/36 ,  F01D5/30

Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a plurality of chord lines spaced apart in a spanwise direction. Each chord line of the plurality of chords lines is defined between the leading edge and the trailing edge and has a normalized chord value. From the hub, the normalized chord value decreases to a minimum value between about 20% to about 90% span and increases from the minimum value to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and fan.

公开(公告)号：US11286779B2

公开(公告)日：2022-03-29

申请号：US16892145

申请日：2020-06-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Repp ,  Bruce Reynolds ,  John Gunaraj

IPC: F02C7/36 ,  F01D5/02 ,  F01D5/30

Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a plurality of chord lines spaced apart in a spanwise direction. Each chord line of the plurality of chords lines is defined between the leading edge and the trailing edge and has a normalized chord value. From the hub, the normalized chord value decreases to a minimum value between about 20% to about 90% span and increases from the minimum value to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and fan.

公开(公告)号：US11371354B2

公开(公告)日：2022-06-28

申请号：US16892152

申请日：2020-06-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Repp ,  Bruce Reynolds ,  John Gunaraj

IPC: F01D5/14

Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil having a leading edge, a trailing edge and a mean camber line. The airfoil has a delta inlet blade angle defined as a difference between a local inlet blade angle defined in a spanwise location, and a root inlet blade angle defined at the root. The delta inlet blade angle decreases in the spanwise direction from the root to a minimum value at greater than 10% span and from the minimum value, the delta inlet blade angle increases to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft or the fan.

公开(公告)号：US20210381385A1

公开(公告)日：2021-12-09

申请号：US16892155

申请日：2020-06-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Repp ,  Bruce Reynolds ,  John Gunaraj ,  Dawn McNamee

IPC: F01D5/14

Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil extending in a spanwise direction from 0% span at a root to 100% span at a tip and having a leading edge and a trailing edge. The airfoil has a plurality of spanwise locations between the root and the tip each having a normalized local maximum thickness. A value of the normalized local maximum thickness decreases from the root to a minimum value and increases from the minimum value to the tip, and the minimum value is within 60% span to 90% span. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to a shaft or a fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and the fan.

公开(公告)号：US20210381382A1

公开(公告)日：2021-12-09

申请号：US16892152

申请日：2020-06-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Repp ,  Bruce Reynolds ,  John Gunaraj

IPC: F01D5/14

Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil having a leading edge, a trailing edge and a mean camber line. The airfoil has a delta inlet blade angle defined as a difference between a local inlet blade angle defined a spanwise location, and a root inlet blade angle defined at the root. The delta inlet blade angle decreases in the spanwise direction from the root to a minimum value at greater than 10% span and from the minimum value, the delta inlet blade angle increases to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and the fan.