Inclination of forward and aft groove walls of casing treatment for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11078805-B2
Application number	US-201916384076-A
Country	US
Kind code	B2
Filing date	Apr 15, 2019
Priority date	Apr 15, 2019
Publication date	Aug 3, 2021
Grant date	Aug 3, 2021

Abstract

A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.

First claim

What is claimed is:

1. A compressor for use in a gas turbine engine, the compressor comprising:
an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine, wherein the airfoil further comprises a blade tip;
a casing, the casing including a radially inward surface; and
a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and
wherein the forward groove wall is operably shaped to generate an aft directed jet,
wherein the groove is wider than the blade tip as measured forward to aft,
wherein the aft groove wall is operably shaped to reduce airflow separation proximate an intersection of the radially inward surface of the casing and the aft groove wall,
wherein the aft groove wall is curved in shape, and
wherein the aft groove wall is convex in shape or the aft groove wall includes a convex portion and a concave portion.

2. The compressor of claim 1 , wherein the forward groove wall is curved in shape.

3. The compressor of claim 2 , wherein the forward groove wall is concave in shape.

4. The compressor of claim 1 , wherein the forward groove wall is oriented at an acute angle relative to the radially inward surface of the casing proximate where the forward groove intersects with the radially inward surface of the casing.

5. The compressor of claim 1 , wherein the aft groove wall is oriented at an obtuse angle relative to the radially inward surface of the casing.

6. The compressor of claim 1 , wherein the casing is located radially outward from the airfoil.

7. A compressor for use in a gas turbine engine, the gas turbine engine comprising:
an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine, wherein the airfoil further comprises a blade tip;
a casing, the casing including a radially inward surface; and
a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall,
wherein the aft groove wall is operably shaped to reduce airflow separation proximate an intersection of the radially inward surface of the casing and the aft groove wall,
wherein the aft groove wall is curved in shape,
wherein the groove is wider than the blade tip as measured forward to aft, and
wherein the aft groove wall is convex in shape or the aft groove wall includes a convex portion and a concave portion.

8. The compressor of claim 7 , wherein the casing is located radially outward from the airfoil.

9. A fan case for use in a gas turbine engine, the fan case being configured to enclose an airfoil rotating about an engine central longitudinal axis of a gas turbine engine, the fan case comprising:
a groove located within the fan case opposite the airfoil, the groove is recessed in a radially outward direction from a radially inward surface of the fan case, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and
wherein the forward groove wall is operably shaped to generate an aft directed jet,
wherein the groove is wider than a blade tip of the airfoil as measured forward to aft,
wherein the aft groove wall is operably shaped to reduce airflow separation proximate an intersection of the radially inward surface of the fan case and the aft groove wall,
wherein the aft groove wall is curved in shape, and
wherein the aft groove wall is convex in shape or the aft groove wall includes a convex portion and a concave portion.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Joly Michael M
• Evans Simon W
• Prasad Dilip
• Medic Gorazd
• Kalitzin Georgi
• Voytovych Dmytro Mykolayovych

Classifications

• F04D29/685 Primary

  Inducing localised fluid recirculation in the stator-rotor interface · CPC title

• F01D11/10 Primary

  using sealing fluid, e.g. steam · CPC title

• F05D2240/55

  Seals · CPC title

• F02C7/28

  Arrangement of seals · CPC title

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title