Trailing edge core compartment vent for an aircraft engine

Patent metadata

Field	Value
Publication number	US-10040560-B2
Application number	US-201514870401-A
Country	US
Kind code	B2
Filing date	Sep 30, 2015
Priority date	Sep 30, 2015
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

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.

First claim

What is claimed is:

1. A turbine engine nozzle, comprising:
a primary outer wall directly coupled to a trailing end of an engine core and extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, the primary outer wall forming a core nozzle; and
a single engine core cowl extending from the engine core area to an annular cowl terminus, the single engine core cowl forming a core compartment vent nozzle,
wherein:
the core compartment vent nozzle is configured to exhaust air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall,
the annular cowl terminus is in substantially planar alignment with the annular wall terminus, and
at the trailing edge between the single engine core cowl and the primary outer wall, the primary outer wall is substantially parallel to the single engine core cowl.

2. The turbine engine nozzle of claim 1 , wherein the core compartment vent nozzle comprises an annulus between the annular cowl terminus of the single engine core cowl and annular wall terminus of the primary outer wall.

3. The turbine engine nozzle of claim 1 , wherein the core compartment vent nozzle comprises a circular annulus around the complete circumference of the engine tail cone.

4. The turbine engine nozzle of claim 3 , wherein the core compartment vent nozzle is configured to vent the air around the entire circumference of the engine tail cone into a trailing edge between a fan air flow flowing outside of the single engine core cowl and a core air flow flowing between the primary outer wall and the engine tail cone.

5. The turbine engine nozzle of claim 1 , wherein the single core cowl comprises only one core cowl and the turbine engine nozzle lacks any other core cowls.

6. The turbine engine nozzle of claim 1 , wherein the turbine engine nozzle lacks any batwing ramp configured to transition the air from the single core cowl.

7. An aircraft engine, comprising
a ducted fan comprising a fan airflow exit configured to exhaust a fan air flow;
a core gas turbine engine comprising:
a core nozzle configured to exhaust a core air flow from the turbine engine core,
a core compartment vent nozzle configured to exhaust a core compartment vent air flow from a core compartment; and
an engine tail cone,

wherein the core compartment vent nozzle is configured to exhaust a compartment vent air flow at a trailing edge between the fan air flow and the core air flow, and
wherein the turbine engine comprises:
a primary outer wall directly coupled to a trailing end of an engine core, and extending from an engine core area to an annular wall terminus that surrounds the engine tail cone, the primary outer wall forming the core nozzle,
a single engine core cowl extending the engine core area to an annular cowl terminus, the single engine core cowl forming a core compartment vent nozzle,
the annular cowl terminus is in substantially planar alignment with the annular wall terminus, and
at the trailing edge between the single engine core cowl and the primary outer wall, the primary outer wall is substantially parallel to the single engine core cowl.

8. The aircraft engine of claim 7 , wherein the core compartment vent nozzle comprises an annular gap between the single engine core cowl and the primary outer wall.

9. The aircraft engine of claim 7 , further comprising:
an engine cover at least partially enclosing the ducted fan and the turbine engine core.

10. An aircraft comprising:
an aircraft body comprising a fuselage and at least one wing; and
at least one aircraft engine, the at least one aircraft engine comprising:
a ducted fan comprising a fan airflow exit for exhausting a fan air flow, and
a turbine engine core comprising:
a core nozzle configured to exhaust a core air flow from the turbine engine core, and
a core compartment vent nozzle configured to exhaust a core compartment vent air flow from a core compartment; and

an engine tail cone,
wherein the core compartment vent nozzle exhausts core compartment vent air flow through a trailing edge between the fan air flow and the core air flow, and
wherein the turbine engine core comprises:
a primary outer wall directly coupled to a trailing end of an engine core, and extending from an engine core area to an annular wall terminus that surrounds the engine tail cone, the primary outer wall forming the core nozzle
a single engine core cowl the engine core area to an annular cowl terminus, the single engine core cowl forming the core compartment vent nozzle,
the annular cowl terminus is in substantially planar alignment with the annular wall terminus, and
at the trailing edge between the single engine core cowl and the primary outer wall, the primary outer wall is substantially parallel to the single engine core cowl.

11. The aircraft of claim 10 , wherein the core compartment vent nozzle comprises an annular gap between the single engine core cowl and the primary outer wall.

12. The aircraft of claim 10 , further comprising:
an engine cover at least partially enclosing the ducted fan and the turbine engine core.

13. The aircraft of claim 10 , wherein the at least one aircraft engine is coupled to the at least one wing.

14. An aircraft engine, comprising:
a ducted fan comprising a fan airflow exit configured to exhaust fan air; and
a turbine engine core comprising:
an engine core;
a tail cone at a trailing end of the engine core;
a primary outer wall around the tail cone, the primary outer wall directly coupling to a trailing edge of the core and extending from an engine core area to an annular wall terminus and forming a core nozzle configured to exhaust core air; and
an engine core cowl around the primary outer wall, the engine cowl extending from the engine core area to an annular cowl terminus forming a core compartment vent nozzle configured to exhaust core vent air,

wherein:
the core compartment vent nozzle comprises a circular annulus around the complete circumference of the tail cone,
the core compartment vent nozzle is configured to exhaust the core vent air around the entire circumference of the tail cone into the trailing edge, between the engine core cowl and the primary outer wall,
the primary outer wall is parallel to the engine core cowl at the trailing edge,
the annular cowl terminus is in planar alignment with the annular wall terminus around the trailing edge,
at the trailing edge between the single engine core cowl and the primary outer wall, the primary outer wall is substantially parallel to the single engine core cowl, and
the turbine engine core lacks any batwing ramp configured to transition the air from the core cowl.

Assignees

• Boeing Co

Inventors

• Willie Robert H
• Tretow Paul R
• Cerra David F

Classifications

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F05D2260/608

  Aeration, ventilation, dehumidification or moisture removal of closed spaces · CPC title

• B64D2033/0273

  for jet engines · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title