Airfoil shroud assembly using tenon with externally threaded stud and nut

Patent metadata

Field	Value
Publication number	US-11028709-B2
Application number	US-201816134344-A
Country	US
Kind code	B2
Filing date	Sep 18, 2018
Priority date	Sep 18, 2018
Publication date	Jun 8, 2021
Grant date	Jun 8, 2021

Abstract

An airfoil and shroud assembly includes an airfoil including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base. A shroud includes an opening configured to receive the base of the tenon. A nut is configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil to couple the shroud to the airfoil.

First claim

What is claimed is:

1. An assembly, comprising:
an airfoil body including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base, wherein the base of the tenon is wider than the externally threaded stud;
a shroud including an opening configured to receive the base of the tenon;
a nut configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil body to couple the shroud to the airfoil body, the nut including an integral washer; and
a bushing having a first internal opening to receive the base of the tenon and for concentrically positioning the base of the tenon within the opening in the shroud, a second internal opening allowing the externally threaded stud to pass therethrough, wherein the first internal opening is wider than the second internal opening, and an external surface configured to engage an inner surface of the opening in the shroud, wherein the bushing has a radially outer surface having a diameter the same as a diameter of the integral washer.

2. The assembly of claim 1 , wherein the root end is configured to be coupled to an outer casing of a turbomachine, and the free end extends radially inward toward a rotor of the turbomachine.

3. The assembly of claim 1 , wherein the shroud includes a plurality of the openings, each opening configured to receive the base of the tenon of a respective airfoil body.

4. A vane for a turbomachine, the vane comprising:
an airfoil body including a free end and a root end, the root end configured to be mounted to an outer casing of the turbomachine;
a tenon extending from a free end of the airfoil body, the tenon including a base configured to be received in an opening in a shroud and an externally threaded stud extending from the base, wherein the base of the tenon is wider than the externally threaded stud;
a nut configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil body to couple the shroud to the airfoil body, the nut including an integral washer; and
a bushing having a first internal opening to receive the base of the tenon and for concentrically positioning the base of the tenon within the opening in the shroud, a second internal opening allowing the externally threaded stud to pass therethrough, wherein the first internal opening is wider than the second internal opening, and an external surface configured to engage an inner surface of the opening in the shroud, wherein the bushing has a radially outer surface having a diameter the same as a diameter of the integral washer.

5. An assembly, comprising:
a vane including an airfoil body including a root end, a free end and a tenon extending from the free end, wherein the root end is configured to be coupled to an outer casing of a turbomachine, and the free end extends radially inward toward a rotor of the turbomachine, and wherein the tenon includes a base and an externally threaded stud extending from the base, wherein the base of the tenon is wider than the externally threaded stud;
a shroud including an opening;
a bushing having a first internal opening to receive the base of the tenon and for concentrically positioning the base of the tenon within the opening in the shroud, a second internal opening allowing the externally threaded stud to pass therethrough, wherein the first internal opening is wider than the second internal opening, and an external surface configured to engage an inner surface of the opening in the shroud; and
a nut configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil body to couple the shroud to the airfoil, the nut including an integral washer, wherein the bushing has a radially outer surface having a diameter the same as a diameter of the integral washer.

6. The assembly of claim 5 , wherein the vane includes a plurality of vanes, and the shroud includes a plurality of the openings, each opening configured to receive the base of the tenon of a respective airfoil body of a respective vane.

Assignees

• Gen Electric

Inventors

• Subramanian Vasantharuban
• Denmark Ronald
• Dhayanandam Prem Navin
• Gutta Richard
• Jha Sanjeev Kumar

Classifications

• F01D9/02

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

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F05D2250/281

  threaded · CPC title

• F05D2260/31

  Retaining bolts or nuts · CPC title