Gas turbine engine airfoil with auxiliary flow channel

Patent metadata

Field	Value
Publication number	US-10280757-B2
Application number	US-201415029802-A
Country	US
Kind code	B2
Filing date	Oct 7, 2014
Priority date	Oct 31, 2013
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading edge and a trailing edge and a flow channel that extends between the pressure side surface and the suction side surface.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a variable area section;
a variable vane disposed within said variable area section;
a blade downstream from said variable vane; and
each of said variable vane and said blade including a flow channel having an inlet at a pressure side surface and an outlet at a suction side surface of an airfoil, each flow channel extending in a curved path in each of a chordwise and spanwise direction, such that a first portion of a core airflow is received in said variable vane flow channel, and a second portion of said core airflow is received in said blade flow channel.

2. The gas turbine engine as recited in claim 1 , wherein at least one of said flow channels includes an outlet positioned upstream from a throat area that extends between said airfoil and an adjacent airfoil.

3. The gas turbine engine as recited in claim 1 , wherein said variable vane flow channel includes an outlet positioned downstream from a throat area that extends between said airfoil and an adjacent airfoil.

4. A method of operating a gas turbine engine, the method comprising:
communicating a portion of core airflow through a flow channel that extends between a pressure side surface and a suction side surface of at least one airfoil of the gas turbine engine;
communicating the portion of airflow into an inlet of the flow channel located along the pressure side surface;
expelling the portion of airflow through an outlet of the flow channel located along the suction side surface;
influencing incidence angle variation of a downstream component with the portion of core airflow;
communicating a second portion of core airflow through a second flow channel of the downstream component, wherein the second flow channel extends between a downstream component pressure side surface and a downstream component suction side surface;
communicating the second portion of airflow into an inlet of the second flow channel located along the downstream component pressure side surface; and
expelling the second portion of airflow through an outlet of the second flow channel located along the downstream component suction side surface, wherein said flow channel extends along a curved path in each of a chordwise and a spanwise direction of said airfoil, and said second flow channel extends in a curved path in each of a chordwise and a spanwise direction of said downstream component.

5. The method as recited in claim 4 , comprising the step of rotating a variable vane prior to the step of communicating.

6. The method as recited in claim 4 , wherein said flow channel includes an outlet positioned upstream from a throat area that extends between said airfoil and an adjacent airfoil.

7. The method as recited in claim 4 , wherein said flow channel includes an outlet positioned downstream from a throat area that extends between said airfoil and an adjacent airfoil.

Assignees

• United Technologies Corp

Inventors

• Kupratis Daniel Bernard
• Schwarz Frederick M

Classifications

• F01D5/145 Primary

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F04D29/682

  by fluid extraction · CPC title

• F01D17/14

  varying effective cross-sectional area of nozzles or guide conduits · CPC title

• F05D2240/123

  related to the pressure side of a stator vane · CPC title

• F05D2260/60

  Fluid transfer · CPC title