Potted stator vane with metal fillet

Patent metadata

Field	Value
Publication number	US-10830074-B2
Application number	US-201816026638-A
Country	US
Kind code	B2
Filing date	Jul 3, 2018
Priority date	Jul 3, 2018
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A vane for use with a stator assembly is disclosed herein. The vane having: an upper mounting portion; a lower mounting portion; an airfoil body extending between the upper mounting portion and the lower mounting portion; a first integrally formed metal fillet located between the upper mounting portion and the airfoil body, the first integrally formed metal fillet defining a first mounting surface located between the upper mounting portion and first integrally formed metal fillet; and a second integrally formed metal fillet located between the lower mounting portion and the airfoil body, the second integrally formed metal fillet defining a second mounting surface located between the lower mounting portion and second integrally formed metal fillet.

First claim

What is claimed is:

1. A vane for use with a stator assembly, the vane comprising:
an upper mounting portion;
a lower mounting portion;
an airfoil body extending between the upper mounting portion and the lower mounting portion;
a first integrally formed metal fillet located between the upper mounting portion and the airfoil body, the first integrally formed metal fillet defining a first mounting surface located between the upper mounting portion and the first integrally formed metal fillet, the first mounting surface extending laterally away from the upper mounting portion; and
a second integrally formed metal fillet located between the lower mounting portion and the airfoil body, the second integrally formed metal fillet defining a second mounting surface located between the lower mounting portion and the second integrally formed metal fillet, the second mounting surface extending laterally away from the lower mounting portion, wherein the first integrally formed metal fillet extends completely around a periphery of the airfoil body and the second integrally formed metal fillet extends completely around another periphery of the airfoil body, wherein a side surface extends from the first mounting surface to the first integrally formed metal fillet and a side surface extends from the second mounting surface to the second integrally formed metal fillet.

2. A stator assembly for a compressor of a gas turbine engine, comprising:
an upper shroud;
a lower shroud;
a plurality of vanes secured to the upper shroud and the lower shroud by a rubber potting, each of the plurality of vanes comprising:
an upper mounting portion;
a lower mounting portion;
an airfoil body extending between the upper mounting portion and the lower mounting portion;
a first integrally formed metal fillet located between the upper mounting portion and the airfoil body, the first integrally formed metal fillet defining a first mounting surface located between the upper mounting portion and the first integrally formed metal fillet, the first mounting surface extending laterally from the upper mounting portion, wherein the rubber potting is located between the first mounting surface, the upper mounting portion and a surface of the upper shroud, the surface of the upper shroud being in a facing spaced relationship with respect to the first mounting surface; and
a second integrally formed metal fillet located between the lower mounting portion and the airfoil body, the second integrally formed metal fillet defining a second mounting surface located between the lower mounting portion and the second integrally formed metal fillet, the second mounting surface extending laterally from the lower mounting portion, wherein the rubber potting is located between the second mounting surface, the lower mounting portion and a surface of the lower shroud, the surface of the lower shroud being in a facing spaced relationship with respect to the second mounting surface.

3. The stator assembly of claim 2 , wherein the first integrally formed metal fillet extends completely around a periphery of the airfoil and the second integrally formed metal fillet extends completely around another periphery of the airfoil.

4. The stator assembly of claim 2 , wherein the compressor is a low pressure compressor.

5. The stator assembly of claim 2 , wherein the stator assembly comprises a plurality of upper shrouds and a plurality of lower shrouds circumferentially aligned with each other.

6. The stator assembly of claim 2 , wherein the upper mounting portion, the first integrally formed metal fillet, the airfoil body, the lower mounting portion, the second integrally formed metal fillet are configured to pass through an opening in either the upper shroud or the lower shroud and the rubber potting secures the upper mounting portion and the first integrally formed metal fillet to the upper shroud and the rubber potting secures the lower mounting portion and the second integrally formed metal fillet to the lower shroud.

7. A stator assembly for a compressor of a gas turbine engine, comprising:
an upper shroud;
a lower shroud;
a plurality of vanes secured to the upper shroud and the lower shroud by a rubber potting, each of the plurality of vanes comprising:
an upper mounting portion;
a lower mounting portion;
an airfoil body extending between the upper mounting portion and the lower mounting portion;
a first integrally formed metal fillet located between the upper mounting portion and the airfoil body, the first integrally formed metal fillet defining a first mounting surface located between the upper mounting portion and the first integrally formed metal fillet, wherein the rubber potting is located between the first mounting surface, the upper mounting portion and a surface of the upper shroud; and
a second integrally formed metal fillet located between the lower mounting portion and the airfoil body, the second integrally formed metal fillet defining a second mounting surface located between the lower mounting portion and the second integrally formed metal fillet, wherein the rubber potting is located between the second mounting surface, the lower mounting portion and a surface of the lower shroud, wherein a side surface extends from the first mounting surface to the first integrally formed metal fillet and a side surface extends from the second mounting surface to the second integrally formed metal fillet.

8. The stator assembly of claim 7 , wherein the upper mounting portion, the first integrally formed metal fillet, the side surface extending from the first integrally formed metal fillet, the airfoil body, the lower mounting portion, the second integrally formed metal fillet, and the side surface extending from the second integrally formed metal fillet, are configured to pass through an opening in the upper shroud and an opening in the lower shroud and the rubber potting secures the upper mounting portion and the first integrally formed metal fillet to the upper shroud and the rubber potting secures the lower mounting portion and the second integrally formed metal fillet to the lower shroud.

9. A method of securing a plurality of vanes to a stator assembly of a gas turbine engine, the method comprising:
inserting a plurality of vanes through a mounting opening on either an upper shroud or a lower shroud, each of the plurality of vanes comprising: an upper mounting portion; a lower mounting portion; an airfoil body extending between the upper mounting portion and the lower mounting portion; a first integrally formed metal fillet located between the upper mounting portion and the airfoil body, the first integrally formed metal fillet defining a first mounting surface located between the upper mounting portion and the first integrally formed metal fillet, the first mounting surface extending laterally away from the upper mounting portion, a second integrally formed metal fillet located between the lower mounting portion and the airfoil body, the second integrally formed metal fillet defining a second mounting surface located between the lower mounting portion and the second integrally formed metal fillet, the second mounting surface extending laterally away from the lower mounting portion; and
bonding the upper mounting portion and the first integrally formed metal fillet to the upper shroud by inserting a rubber potting through an opening in the upper shroud, wherein the rubber potting is located between the first mounting surface, the upper mounting portion and a surface of the upper shroud, the surface of the upper shroud being in a facing spaced relationship with respect to the first mounting surface; and
bonding the lower mounting portion and the second integrally formed metal fillet to t

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Freeman Thomas
• Barainca Brian

Classifications

• F05D2240/91

  on a stationary structure · CPC title

• Y10T29/49323

  Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F05D2300/501

  Elasticity · CPC title