公开(公告)号：US20220010732A1

公开(公告)日：2022-01-13

申请号：US17488690

申请日：2021-09-29

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Bruce L. Morin ,  David A. Topol ,  Detlef Korte

IPC: F02C7/24 ,  F02K3/06 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D15/12 ,  F01D17/10 ,  F01D5/16 ,  F01D25/04 ,  F02C3/107 ,  F02C7/36

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.

公开(公告)号：US11719161B2

公开(公告)日：2023-08-08

申请号：US17488690

申请日：2021-09-29

Applicant: RAYTHEON TECHNOLOGIES CORPORATION ,  MTU AERO ENGINES AG

Inventor： Bruce L. Morin ,  David A. Topol ,  Detlef Korte

IPC: F01D5/02 ,  F02C7/24 ,  F02K3/06 ,  F01D5/12 ,  F01D9/04 ,  F01D15/12 ,  F01D17/10 ,  F01D5/16 ,  F01D25/04 ,  F02C3/107 ,  F02C7/36

CPC classification number: F02C7/24 ,  F01D5/02 ,  F01D5/12 ,  F01D5/16 ,  F01D9/041 ,  F01D15/12 ,  F01D17/105 ,  F01D25/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2200/36 ,  F05D2210/31 ,  F05D2220/32 ,  F05D2220/327 ,  F05D2240/301 ,  F05D2240/307 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/60

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.

公开(公告)号：US11560849B2

公开(公告)日：2023-01-24

申请号：US17503814

申请日：2021-10-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION ,  MTU Aero Engines GmbH

Inventor： Bruce L. Morin ,  David A. Topol ,  Detlef Korte

IPC: F02C7/24 ,  F02K3/06 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D15/12 ,  F01D17/10 ,  F01D5/16 ,  F01D25/04 ,  F02C3/107 ,  F02C7/36

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section including a propulsor, a turbine section including a first turbine and a second turbine, a compressor section driven by the turbine section, the compressor section including a first compressor and a second compressor, and a geared architecture driven by the first turbine. The propulsor is driven by the first turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to 0.5 at an approach speed.

公开(公告)号：US20230296114A1

公开(公告)日：2023-09-21

申请号：US18201875

申请日：2023-05-25

Applicant: RAYTHEON TECHNOLOGIES CORPORATION ,  MTU Aero Engines AG

Inventor： Bruce L. Morin ,  Detlef Korte

IPC: F04D29/66 ,  F02C3/107 ,  F02K3/04 ,  G06F30/17 ,  F01D15/12 ,  F04D29/32 ,  F01D5/14 ,  F02C3/04 ,  F02K3/06 ,  F01D5/06 ,  F01D25/24 ,  F02C7/36 ,  F04D25/04 ,  F04D29/053

CPC classification number: F04D29/663 ,  F02C3/107 ,  F02K3/04 ,  G06F30/17 ,  F01D15/12 ,  F04D29/325 ,  F01D5/14 ,  F02C3/04 ,  F02K3/06 ,  F01D5/06 ,  F01D25/24 ,  F02C7/36 ,  F04D25/045 ,  F04D29/053 ,  F04D29/321 ,  F05D2260/40311 ,  F05D2260/96 ,  F05D2270/304 ,  F05D2270/333 ,  F05D2230/50 ,  F05D2220/323

Abstract: An aircraft system includes, among other things, an aircraft and a gas turbine engine coupled to the aircraft. The gas turbine engine includes a propulsor section including a propulsor, a compressor section, a turbine section including a first turbine and a second turbine, and a gear reduction between the propulsor and the second turbine. The second turbine includes a number of turbine blades in each of a plurality of rows of the second turbine. The second turbine blades operating at least some of the time at a rotational speed. The number of blades and the rotational speed being such that the following formula holds true for a majority of the blade rows of the second turbine: 5500 Hz≤(number of blades×speed)/60 sec≤10000 Hz. The gas turbine engine is rated to produce 15,000 pounds of thrust or more.

公开(公告)号：US12123432B2

公开(公告)日：2024-10-22

申请号：US18201875

申请日：2023-05-25

Applicant: RAYTHEON TECHNOLOGIES CORPORATION ,  MTU Aero Engines AG

Inventor： Bruce L. Morin ,  Detlef Korte

IPC: F02C7/36 ,  F01D5/06 ,  F01D5/14 ,  F01D15/12 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02K3/04 ,  F02K3/06 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F04D29/66 ,  G06F30/17

CPC classification number: F04D29/663 ,  F01D5/06 ,  F01D5/14 ,  F01D15/12 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/04 ,  F02K3/06 ,  F04D25/045 ,  F04D29/053 ,  F04D29/321 ,  F04D29/325 ,  G06F30/17 ,  F05D2220/323 ,  F05D2230/50 ,  F05D2260/40311 ,  F05D2260/96 ,  F05D2270/304 ,  F05D2270/333

Abstract: An aircraft system includes, among other things, an aircraft and a gas turbine engine coupled to the aircraft. The gas turbine engine includes a propulsor section including a propulsor, a compressor section, a turbine section including a first turbine and a second turbine, and a gear reduction between the propulsor and the second turbine. The second turbine includes a number of turbine blades in each of a plurality of rows of the second turbine. The second turbine blades operating at least some of the time at a rotational speed. The number of blades and the rotational speed being such that the following formula holds true for a majority of the blade rows of the second turbine: 5500 Hz≤(number of blades×speed)/60 sec≤10000 Hz. The gas turbine engine is rated to produce 15,000 pounds of thrust or more.