Seals for gas turbine engine nacelle cowlings

Patent metadata

Field	Value
Publication number	US-9835092-B2
Application number	US-201514788135-A
Country	US
Kind code	B2
Filing date	Jun 30, 2015
Priority date	Jun 30, 2015
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

A gas turbine engine includes an engine core and core nacelle cowling coupled to the engine core. The engine core has a core member that extends radially outward from the engine core. The core nacelle cowling has a cowling member that extends radially inward towards the engine core. The cowling member is offset axially from the core member to form a labyrinth seal that bounds a coolant inlet, thereby fluidly coupling the fan duct flow of the gas turbine engine with a core compartment defined between the engine core and core nacelle cowling.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
an engine core;
a core nacelle cowling coupled to the engine core, a core compartment with a coolant inlet defined between the core nacelle cowling and the engine core, and at least one component disposed within the core compartment, axially downstream of the coolant inlet; and
wherein, the core nacelle cowling has a labyrinth seal bounding the coolant inlet, wherein the labyrinth seal is formed by:
a plurality of axially spaced core members extending radially outward from the core; and
a plurality of axially spaced cowling members extending radially inward from the core nacelle cowling and being interleaved with the plurality of axially spaced core members by axially and radially overlapping one another to define a tortuous coolant inlet flow path extending between a fan duct flow path and the core compartment; and

wherein the coolant inlet is oriented to direct the tortuous coolant inlet flow path to the component.

2. A gas turbine engine as recited in claim 1 , wherein the labyrinth seal includes a drain mast disposed on a nacelle cowling lower surface and in fluid communication with the coolant inlet.

3. A gas turbine engine as recited in claim 2 , wherein the drain mast is connected to a forward facing surface of the plurality of axially spaced core members to receive liquid therefrom.

4. A gas turbine engine as recited in claim 2 , wherein the drain mast is connected to a forward facing surface of the plurality of axially spaced cowling members to receive liquid therefrom.

5. A gas turbine engine as recited in claim 1 , wherein the plurality of axially spaced cowling members is adjacent to a forward edge of the core nacelle cowling.

6. A gas turbine engine as recited in claim 1 , further including a coolant outlet disposed aft of the coolant inlet at an aft end of the core nacelle cowling.

7. A gas turbine engine as recited in claim 1 , wherein the plurality of axially spaced cowling members is an inlet first cowling member, and further including an inlet second cowling member disposed on a side of the plurality of axially spaced core members opposite the inlet first cowling member.

8. A gas turbine engine as recited in claim 7 , wherein the inlet first cowling member, the plurality of axially spaced core members, and the inlet second cowling member bound the coolant inlet.

9. A gas turbine engine as recited in claim 7 , further including a coolant outlet disposed at an aft end of the core nacelle cowling.

10. A gas turbine engine as recited in claim 1 , wherein the plurality of axially spaced core members is an inlet first core member, and further including a second core member disposed on a side of the plurality of axially spaced cowling members opposite the inlet first core member.

11. A gas turbine engine as recited in claim 10 , wherein the inlet first core member, the plurality of axially spaced cowling members, and the inlet second core member bound the coolant inlet.

12. A gas turbine engine as recited in claim 10 , further including a coolant outlet disposed at an aft end of the core nacelle cowling.

13. A gas turbine engine as recited in claim 1 , wherein the core nacelle cowling presents a continuous surface to the core compartment downstream of the coolant inlet.

14. A gas turbine engine of claim 1 , further comprising a bypass nacelle coupled to the engine core and circumferentially surrounding the core nacelle cowling to define a bypass duct therebetween that is in fluid communication with the core compartment through the coolant inlet.

15. A gas turbine engine as recited in claim 14 , further including an engine core bleed conduit in fluid communication with the engine core and disposed within the core compartment.

16. A gas turbine engine as recited in claim 14 , further including a drain mast with a drain outlet in fluid communication with the labyrinth seal, the drain outlet disposed on an exterior of the bypass nacelle.

17. A gas turbine engine as recited in claim 14 , further including a core compartment coolant outlet disposed aft of the coolant inlet.

18. A gas turbine engine as recited in claim 17 , wherein the core nacelle cowling presents a continuous surface to the core compartment downstream of the coolant inlet.

Assignees

• United Technologies Corp

Inventors

• Sawyers-Abbott Nigel D
• Reinhardt Gregory E

Classifications

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F05D2240/55

  Seals · CPC title

• F01D11/02

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title