David F Cerra from Highlands Ranch, CO, age 43

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Gas Turbine Engine Nozzle Configurations
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US Patent:

8356468, Jan 22, 2013
Filed:

Jun 12, 2009
Appl. No.:

12/483424
Inventors:

David F. Cerra - Bellevue WA, US
Lie-Mine Gea - Irvine CA, US
Robert H. Willie - Bothell WA, US
Leonard J. Herbert - Kirkland WA, US
Donald E. Robinson - Mercer Island WA, US
Assignee:

The Boeing Company - Chicago IL
International Classification:

F02K 1/48
B64G 1/40
F02K 1/38
US Classification:

60262, 60264, 60770, 23926519
Abstract:

In one embodiment, a gas turbine engine exhaust nozzle comprises a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface, and a row of chevrons extending from an aft end of the housing, the chevrons having a root region and a tip, wherein at least a portion of at least one of the interior surface or the exterior surface is scalloped proximate the root region of a chevron. Other embodiments may be described.

Sheared Exhaust Nozzle
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US Patent:

20220205409, Jun 30, 2022
Filed:

Mar 15, 2022
Appl. No.:

17/695560
Inventors:

- Chicago IL, US
David F. Cerra - Woodinville WA, US
Robert H. Willie - Freeland WA, US
Assignee:

The Boeing Company - Chicago IL
International Classification:

F02K 1/46
F02K 3/06
Abstract:

Conventional commercial engine exhaust systems are defined with axi-symmetric surfaces (e.g., conical or nearly conical surfaces), which create an annular exhaust for the fan (bypass) nozzle of roughly constant duct-height around the circumference. In one example configuration, the fan sleeve has been sheared upward (towards the wing or pylon) causing a larger area and duct height near the pylon relative to the portion away from the pylon. For a given thrust generated by the turbofan engine housed in the nacelle, the shear toward the pylon mount realigns the thrust in the direction of flight which may, in some examples, reduce noise experienced downstream of the turbofan engine and decreases fuel consumed in the engine core.

Aircraft Engine Exhaust Systems Enabling Reduced Length Aft Strut Fairings
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US Patent:

20210094699, Apr 1, 2021
Filed:

Sep 27, 2019
Appl. No.:

16/586133
Inventors:

- Chicago IL, US
David F. Cerra - Woodinville WA, US
International Classification:

B64D 33/04
B64D 27/18
B64D 29/06
F02C 7/24
F02C 7/20
Abstract:

Aircraft engine exhaust systems enabling short aft fairings are described. An example turbofan engine exhaust system of an aircraft includes a primary nozzle having a leading edge and a trailing edge, and a heat shield coupled to an aft strut fairing. The heat shield has an upstream end and a downstream end. The downstream end of the heat shield is substantially coterminous with the trailing edge of the primary nozzle.

Sheared Exhaust Nozzle
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US Patent:

20200224605, Jul 16, 2020
Filed:

Jan 15, 2019
Appl. No.:

16/248342
Inventors:

- Chicago IL, US
David F. Cerra - Woodinville WA, US
Robert H. Willie - Freeland WA, US
Assignee:

The Boeing Company - Chicago IL
International Classification:

F02K 1/46
F02K 3/06
Abstract:

Conventional commercial engine exhaust systems are defined with axi-symmetric surfaces (e.g., conical or nearly conical surfaces), which create an annular exhaust for the fan (bypass) nozzle of roughly constant duct-height around the circumference. In one example configuration, the fan sleeve has been sheared upward (towards the wing or pylon) causing a larger area and duct height near the pylon relative to the portion away from the pylon. For a given thrust generated by the turbofan engine housed in the nacelle, the shear toward the pylon mount realigns the thrust in the direction of flight which may, in some examples, reduce noise experienced downstream of the turbofan engine and decreases fuel consumed in the engine core.

Trailing Edge Core Compartment Vent For An Aircraft Engine
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US Patent:

20170088275, Mar 30, 2017
Filed:

Sep 30, 2015
Appl. No.:

14/870401
Inventors:

- Chicago IL, US
Paul R. Tretow - Mukilteo WA, US
David F. Cerra - Woodinville WA, US
International Classification:

B64D 27/12
F02K 1/82
B64D 29/00
F02K 3/04
Abstract:

A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall.

Ventilated Drainage System
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US Patent:

20150361999, Dec 17, 2015
Filed:

Jun 12, 2014
Appl. No.:

14/302676
Inventors:

- Chicago IL, US
David F. Cerra - Woodinville WA, US
International Classification:

F15D 1/00
B64D 29/00
B64D 37/00
Abstract:

A method and apparatus for draining fluid from a structure on an aircraft. The apparatus comprises a drainage tube, a housing, a number of inlet holes in the housing, and a number of outlet holes in the housing. The drainage tube has first end that connects to a structure on an aircraft and a second end opposite the first end. The housing connects to the structure. The drainage tube is located within the housing. Air flows into the housing during flight of the aircraft through the number of inlet holes in the housing. The air flows out of the housing during flight of the aircraft through the number of outlet holes. The air flowing into the housing through the number of inlet holes and out the housing through the number of outlet holes directs fluid out of the drainage tube and away from the structure during flight of the aircraft.

Methods And Apparatus For Passive Thrust Vectoring And Plume Deflection
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US Patent:

20150113946, Apr 30, 2015
Filed:

Oct 24, 2013
Appl. No.:

14/062673
Inventors:

- Chicago IL, US
David F. Cerra - Bellevue WA, US
Leonard J. Hebert - Kirkland WA, US
Assignee:

The Boeing Company - Chicago IL
International Classification:

F02K 1/00
US Classification:

60228
Abstract:

A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.

Gas Turbine Engine Nozzle Including Housing Having Scalloped Root Regions
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US Patent:

20140202164, Jul 24, 2014
Filed:

Jan 21, 2013
Appl. No.:

13/746277
Inventors:

David F. Cerra - Bellevue WA, US
Lie-Mine Gea - Irvine CA, US
Robert H. Willie - Bothell WA, US
Leonard J. Hebert - Kirkland WA, US
Donald E. Robinson - Mercer Island WA, US
International Classification:

F02K 9/97
US Classification:

60770
Abstract:

A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons. The scalloped root regions have a reduced thickness relative to the rest of the aft end.