Guide vane of a gas turbine engine, in particular of an aircraft engine

Patent metadata

Field	Value
Publication number	US-10634006-B2
Application number	US-201615194797-A
Country	US
Kind code	B2
Filing date	Jun 28, 2016
Priority date	Jul 1, 2015
Publication date	Apr 28, 2020
Grant date	Apr 28, 2020

Abstract

A guide vane of a gas turbine engine, in particular of an aircraft engine, which has a pressure-side wall, a suction-side wall, a guide vane root, a guide vane tip, a guide vane leading edge area that is impinged by a cooling air flow of a cooling system, a guide vane trailing edge area that is facing away from the guide vane leading edge area, and at least one channel for conducting a fluid to be cooled arranged in an internal space of the guide vane. At that, during operation of the gas turbine engine, a first part of the cooling air flow flows around a pressure-side wall, and a second part of the cooling air flow flows around the suction-side wall, and a third part of the cooling air flow flows through the internal space including the channel. What is further suggested is a gas turbine engine with at least one such static guide vane.

First claim

The invention claimed is:

1. A guide vane of a gas turbine aircraft engine comprising:
a concave pressure-side wall;
a convex suction-side wall opposite and facing away from the concave pressure-side wall;
a guide vane root;
a guide vane tip;
an internal space of the guide vane;
a guide vane leading edge area which directs a first part of a cooling air flow around the concave pressure-side wall, a second part of the cooling air flow around the convex suction-side wall, and a third part of the cooling air flow through the internal space of the guide vane;
a fluid conducting cooling channel arranged in the internal space of the guide vane and exposed to the third part of the cooling air flow through the internal space; and
a guide vane trailing edge area facing away from the guide vane leading edge area;
wherein the internal space of the guide vane connects to an air inlet opening arranged in the guide vane leading edge area to direct the third part of the cooling air flow through the internal space of the guide vane, and wherein the internal space of the guide vane connects to an air outlet opening arranged in the guide vane trailing edge area; and
a particle deflector formed as a lip which protrudes over the air inlet opening in the guide vane leading edge area.

2. The guide vane according to claim 1 , wherein the particle deflector is curved such that a direction of the cooling air flow is changed as the cooling air flow flows in the internal space.

3. The guide vane according to claim 1 , wherein the particle deflector protrudes over the air inlet opening by a clearance that is determined by a distance between the concave pressure-side wall and the convex suction-side wall such that the third part of the cooling air flow flows into the air inlet opening between the lip and the concave pressure-side wall with a flow direction that is oriented towards the convex suction-side wall.

4. The guide vane according to claim 1 , further comprising a plurality of ribs in contact with at least one chosen from the concave pressure-side wall and the convex suction-side wall, and wherein the plurality of ribs are arranged in the internal space of the guide vane and exposed to the third part of the cooling air flow through the internal space.

5. The guide vane according to claim 4 , wherein the plurality of ribs extend in a direction from the guide vane leading edge area to the guide vane trailing edge area.

6. The guide vane according to claim 4 , wherein the plurality of ribs are in contact with the fluid conducting cooling channel.

7. The guide vane according to claim 4 , wherein at least part of the fluid conducting cooling channel passes through the plurality of ribs.

8. The guide vane according to claim 1 , wherein the fluid conducting cooling channel is arranged in a meandering shape in the internal space of the guide vane.

9. The guide vane according to claim 1 , further comprising:
a fluid inlet of the fluid conducting cooling channel, wherein the fluid inlet is arranged for taking in a fluid to be cooled from a hot fluid conduit, and
a fluid outlet of the fluid conducting cooling channel, wherein the fluid outlet is arranged at the guide vane root to discharge a cooled fluid from the guide vane into a cold fluid conduit.

10. The guide vane according to claim 1 , wherein the internal space of the guide vane is divided into multiple chambers.

11. A gas turbine engine, comprising the guide vane according to claim 1 , wherein the guide vane is arranged in a bypass channel or a core flow channel of the gas turbine engine.

12. A guide vane of a gas turbine aircraft engine comprising:
a pressure-side wall;
a suction-side wall;
an internal space of the guide vane;
a guide vane leading edge area which directs a first part of a cooling air flow around the pressure-side wall, a second part of the cooling air flow around the suction-side wall, and a third part of the cooling air flow through the internal space of the guide vane;
a fluid conducting cooling channel arranged in the internal space of the guide vane and exposed to the third part of the cooling air flow through the internal space;
a guide vane trailing edge area facing away from the guide vane leading edge area;
a cooling air flow diverter;
a lip, wherein the lip forms the cooling air flow diverter; and
an air inlet opening, wherein the lip protrudes over the air inlet opening in the area of the guide vane leading edge.

13. The guide vane according to claim 12 , wherein the lip protrudes over the air inlet opening by a clearance that is determined by a distance between the pressure-side wall and the suction-side wall such that the cooling air flow flows into the air inlet opening between the lip and the pressure-side wall with a flow direction that is substantially oriented towards the suction-side wall.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Todorovic Predrag

Classifications

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2240/121

  related to the leading edge of a stator vane · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F05D2260/22141

  using fins or ribs · CPC title