Jonathan Scott Rivers

US Patent:

20110305577, Dec 15, 2011

Filed:

Jun 15, 2010

Appl. No.:

12/815571

Inventors:

JONATHAN M. RIVERS - Danville IN, US
Matthew A. Scott - Melbourne, GB

International Classification:

F01D 5/14
B21K 3/04

US Classification:

416223 R, 298897

Abstract:

An aggregate vane assembly is disclosed herein. The aggregate vane assembly includes a core vane assembly encircling a central longitudinal axis. The core vane assembly has a plurality of core vanes each extending radially between an inner hub and an outer band. The core vane assembly extends along the central longitudinal axis between a first forward end and a first aft end. The aggregate vane assembly also includes a bypass vane assembly disposed on a radially opposite side of the outer band relative to the plurality of core vanes. The bypass vane assembly includes at least one bypass vane extending radially outward from a platform. The bypass vane assembly extends along the central longitudinal axis between a second forward end and a second aft end. The aggregate vane assembly also includes at least one boss fixed with the outer band and operable to engage the bypass vane assembly proximate to the second forward end.

US Patent:

20210381396, Dec 9, 2021

Filed:

Jun 3, 2020

Appl. No.:

16/891928

Inventors:

- Indianapolis IN, US
Robert Heeter - Noblesville IN, US
Jonathan Michael Rivers - Indianapolis IN, US
Benedict N. Hodgson - Indianapolis IN, US

International Classification:

F01D 25/24
F01D 25/00
F01D 21/04

Abstract:

The disclosure describes composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

US Patent:

20210355833, Nov 18, 2021

Filed:

May 12, 2020

Appl. No.:

15/930158

Inventors:

- Indianapolis IN, US
Matthew J. Kappes - Greenwood IN, US
Jonathan Michael Rivers - Indianapolis IN, US
Benedict N. Hodgson - Indianapolis IN, US

International Classification:

F01D 5/28
F01D 9/02

Abstract:

A composite aerofoil may include an aerofoil body defining a leading edge and a trailing edge, wherein the body comprises a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements. The disclosure also describes techniques for forming composite aerofoils.

US Patent:

20200392872, Dec 17, 2020

Filed:

Jun 11, 2019

Appl. No.:

16/437966

Inventors:

- Indianapolis IN, US
Jonathan Rivers - Indianapolis IN, US
Robert Heeter - Noblesville IN, US

International Classification:

F01D 25/28
F02C 7/20

Abstract:

An assembly fixture for a fan casing of a gas turbine engine wherein the fan casing includes a casing having a flange with a plurality of apertures extending therethrough, comprises a locating structure having a positioning feature that is engageable by a fastener extending through a particular aperture of the plurality of apertures to secure the locating structure to the fan casing. The locating structure further includes a locating feature indicating a particular location of the fan casing when the locating structure is mounted to the fan casing.

US Patent:

20180258852, Sep 13, 2018

Filed:

Mar 7, 2017

Appl. No.:

15/452341

Inventors:

- Indianapolis IN, US
Jonathan Rivers - Indianapolis IN, US
Dennes Kyle Burney - Indianapolis IN, US

International Classification:

F02C 7/045

Abstract:

An aircraft engine includes a rotating structure and a casing circumferentially surrounding the rotating structure. The aircraft engine further includes an acoustic panel for noise reduction circumferentially surrounding the rotating structure. The acoustic panel is disposed proximal the casing. Furthermore, the acoustic panel includes a plurality of acoustic panel members. In addition, the acoustic panel is secured to the casing by at least one securement mechanism such that the acoustic panel is substantially circumferentially fixed relative to the casing.

US Patent:

20180258954, Sep 13, 2018

Filed:

Mar 7, 2017

Appl. No.:

15/452311

Inventors:

- Indianapolis IN, US
Jonathan Rivers - Indianapolis IN, US
Dennes Kyle Burney - Indianapolis IN, US

International Classification:

F04D 29/66
F04D 29/52
F04D 29/64
F02K 3/06

Abstract:

An aircraft engine includes a rotating structure and a casing circumferentially surrounding the rotating structure. The aircraft engine further includes an acoustic panel for noise reduction circumferentially surrounding the rotating structure and disposed adjacent the casing. The acoustic panel comprises a plurality of acoustic panel members arranged adjacent to one another to form a substantially complete ring of the acoustic panel. A first acoustic panel member of the plurality of acoustic members is adjacent to a second acoustic panel member of the plurality of acoustic members. The first acoustic panel member is removably secured to the second acoustic panel member by a releasable fastening assembly.

US Patent:

20180231016, Aug 16, 2018

Filed:

Oct 28, 2016

Appl. No.:

15/338035

Inventors:

- Indianapolis IN, US
Jonathan M. Rivers - Indianapolis IN, US

International Classification:

F04D 29/28
F04D 29/34
B64C 11/06
B63H 1/16
B23K 101/00
F04D 29/32
B64C 11/00

Abstract:

A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.

US Patent:

20180119705, May 3, 2018

Filed:

Oct 28, 2016

Appl. No.:

15/337936

Inventors:

- Indianapolis IN, US
Jonathan M. Rivers - Indianapolis IN, US

International Classification:

F04D 29/32
F04D 29/02
F04D 19/00
B64C 11/00
B64C 11/48

Abstract:

A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees. Passive leading edge slats are attached to the ring airfoil and are configured to open and close using springs.