公开(公告)号：US20210317753A1

公开(公告)日：2021-10-14

申请号：US16846981

申请日：2020-04-13

Applicant: Raytheon Technologies Corporation

Inventor： Ramons A. Reba

IPC: F01D25/04 ,  F01N1/02

Abstract: Acoustic treatments for components of gas turbine engines are described. The acoustic treatments include an acoustic resonator having a backing chamber defining a respective volume and a neck arranged relative to the backing chamber and defining an opening, wherein the neck has a length and a cross-sectional area. The acoustic resonator cell satisfies the following relationships: (1) l/L=0.2-0.8, where l is a length of the neck and L is a depth of the backing chamber and (2) a/A=0.02-0.20, where a is a cross-sectional area of the neck and A is a cross-sectional area of the backing chamber.

公开(公告)号：US11118507B2

公开(公告)日：2021-09-14

申请号：US16867668

申请日：2020-05-06

Applicant: Raytheon Technologies Corporation

Inventor： Jonathan Gilson ,  Bruce L. Morin ,  Ramons A. Reba ,  David A. Topol ,  Wesley K. Lord

IPC: F02C3/107 ,  F01D9/04 ,  F04D29/54 ,  F01D25/16 ,  F04D29/66 ,  F02K3/06

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

公开(公告)号：US20230117838A1

公开(公告)日：2023-04-20

申请号：US17503285

申请日：2021-10-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Craig Aaron Reimann ,  Julian Winkler ,  Kenji Homma ,  Jeffrey Michael Mendoza ,  Ramons A. Reba

IPC: G10K11/16 ,  F02C7/24

Abstract: An acoustic attenuation structure for a gas turbine engine includes a periodic structure having a first unit cell, the first unit cell having a first central body and a first axial tube disposed on the first central body and a second axial tube disposed on the first central body, opposite the first axial tube, each of the first axial tube and the second axial tube being in fluid communication with one another through the first central body.

公开(公告)号：US11199107B2

公开(公告)日：2021-12-14

申请号：US16846981

申请日：2020-04-13

Applicant: Raytheon Technologies Corporation

Inventor： Ramons A. Reba

IPC: F01D25/04 ,  F01N1/02

Abstract: Acoustic treatments for components of gas turbine engines are described. The acoustic treatments include an acoustic resonator having a backing chamber defining a respective volume and a neck arranged relative to the backing chamber and defining an opening, wherein the neck has a length and a cross-sectional area. The acoustic resonator cell satisfies the following relationships: (1) l/L=0.2-0.8, where l is a length of the neck and L is a depth of the backing chamber and (2) a/A=0.02-0.20, where a is a cross-sectional area of the neck and A is a cross-sectional area of the backing chamber.

公开(公告)号：US20210372323A1

公开(公告)日：2021-12-02

申请号：US17399309

申请日：2021-08-11

Applicant: Raytheon Technologies Corporation

Inventor： Jonathan Gilson ,  Bruce L. Morin ,  Ramons A. Reba ,  David A. Topol ,  Wesley K. Lord

IPC: F02C3/107 ,  F01D9/04 ,  F04D29/54 ,  F01D25/16 ,  F04D29/66 ,  F02K3/06

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

公开(公告)号：US11830467B2

公开(公告)日：2023-11-28

申请号：US17503285

申请日：2021-10-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Craig Aaron Reimann ,  Julian Winkler ,  Kenji Homma ,  Jeffrey Michael Mendoza ,  Ramons A. Reba

IPC: G10K11/16 ,  F02C7/24

CPC classification number: G10K11/16 ,  F02C7/24 ,  F05D2220/323 ,  F05D2260/96

Abstract: An acoustic attenuation structure for a gas turbine engine includes a periodic structure having a first unit cell, the first unit cell having a first central body and a first axial tube disposed on the first central body and a second axial tube disposed on the first central body, opposite the first axial tube, each of the first axial tube and the second axial tube being in fluid communication with one another through the first central body.

公开(公告)号：US11512631B2

公开(公告)日：2022-11-29

申请号：US17399309

申请日：2021-08-11

Applicant: Raytheon Technologies Corporation

Inventor： Jonathan Gilson ,  Bruce L. Morin ,  Ramons A. Reba ,  David A. Topol ,  Wesley K. Lord

IPC: F02C3/10 ,  F01D9/04 ,  F04D29/54 ,  F01D25/16 ,  F04D29/66 ,  F02K3/06 ,  F02C3/107

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.