Aft mounting system for combustion transition duct members

• US 4,422,288 A
• Filed: 03/02/1981
• Issued: 12/27/1983
• Est. Priority Date: 03/02/1981
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Steber, Charles E.
• Primary Examiner(s): Garrett, Robert E.
• Application Number:
  US06/239,437
• Time in Patent Office: 1,030 Days
• Field of Search: 60/39.37, 60/39.32, 60/39.31, 60/261, 60/752, 248/55, 248/65, 248/58, 248/571
• US Class Current: 60/800
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F16L 3/16 with special provision allowing movement of the pipe F16L3/01 takes precedence; supporting pipes or cables inside other pipes or sleeves F16L7/00
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means

Abstract

A structural support system for the aft end of advanced design combustion transition duct members of specially configured to withstand high temperature gradients and mechanical loads developed in heavy-duty cannular gas turbine combustion systems. A composite element support system is provided for each transition duct member wherein one end of a cylindrical base element is contoured for and welded to the outer wall of its associated transition duct member, while its other end carries a hinge joint of special design to interconnect the transition duct member to a desired mounting member. The circular footprint of the cylindrical base element on the transition duct member wall is configured to minimize thermal and mechanical stresses especially in the weld joint region, while the hinge joint allows relative movement of the connected parts about a desired axis. Additionally, a hinge joint through bolt is torqued to a predetermined value to dampen out unwanted mechanical vibrations.

Claims

1. A support system for attaching the aft end of a gas turbine combustion transition duct member to a functionally related structural member comprising:

(a) a cylindrical shaped base member contoured to mate with the surface of said transition duct member and rigidly attached thereto;

(b) a pivoting hinge assembly comprising;

(i) boss means rigidly attached to said base member;

(ii) a bracket having a first end adapted to be nested with said boss means and to be nested with said boss means and a second end adapted to be attached to said functionally related structural member;

(iii) interconnecting means fitted through said boss and said bracket for retaining said boss means and said bracket in close cooperating relationship, and providing a pivot axis for enabling pivotal relative motion therebetween; and

(iv) said interconnecting means being configured to apply a predetermined force between said boss means and said bracket to resist, in controlled part, said pivotal relative motion.

2. The support system of claim 1 wherein said interconnecting means includes a thorough bolt-retaining nut assembly to apply said pre-determined force by adjustably advancing said nut on said bolt.

3. The support in claim 1 wherein said base member is welded to the outer wall of the aft end of said transition piece.

4. The support of claim 1 wherein the gas turbine combustion system is of the cannular type having a plurality of transition duct members circumferentially arrayed about a major longitudinal axis and said support system comprises a like plurality of base members and pivoting hing assemblies to provide attachment of the aft end of each of said plurality of transition duct members to the structural member of the gas turbine.

5. The support system of claim 4 wherein each of said plurality of base members is welded to the radially outboard wall of the aft end of each of said circumferentially arrayed transition duct members.

6. An improved support system for the aft end of combustion transition ducts of a gas turbine comprising:

(a) a cylindrically shaped base member contoured to mate with the radially outboard surface of the aft end of a transition duct member and being attached thereto;

(b) a hinge assembly comprising;

(i) at least one boss member rigidly attached to said base member;

(ii) a bracket shaped to cooperatively nest with said at least one boss member at a first bracket end, and rigidly attached via a second bracket end to a selected supporting member within said gas turbine;

(iii) interconnecting means fitted through said boss member and said bracket for retaining said boss member and said bracket in close cooperating nested relationship, and providing a pivot axis for enabling pivotal relative motion therebetween.

(iv) said interconnecting means configured to apply a predetermined force between said boss member and said bracket to resist, in controlled part, said pivotal relative motion.

7. The improved support system of claim 6 having a pair of boss members aligned along said pivot axis and symmetrically attached to said base member, said bracket cooperatively nesting between said bosses.

8. The improved support system of claim 7 further comprising a pair of hardened washers positioned between said pair of bosses and said cooperatively nested bracket for providing wear-resistant surfaces therebetween.

9. The improved support system of claim 7 further comprising a pair of bushings axially positioned by and extending through said pair of bosses and extending into said bracket along said pivot axis for providing bearing surfaces for said pivotal action between said bracket and said bosses.

10. The improved support system of claim 9 further comprising a through bolt-retaining nut assembly along said pivot axis inside said bushings to apply said predetermined force by adjustably advancing said nut on said bolt.

11. The improved support of claim 6 wherein said pivotal action permits relative movement between said transition duct member and said selected support member about a desired direction only.

12. The improved support system of claim 6 wherein said base member is cylindrically shaped to permit a continuous, circular weld joint between the transition duct wall and said base member to minimize stress concentrations and to eliminate end effects in said weld joint.

13. The improved support system of claim 12 wherein the cylinder is of selected wall thickness to minimize thermal and mechanical stresses in the cylinder to said duct wall weld joint as well as in the duct wall and cylinder wall in the vicinity of said weld joint.

14. The improved support system of claim 6 wherein the cylindrical member is fabricated integral with a contoured base member which duplicates a portion of the duct wall and replaces said duct wall portion when welded to the remainder of said duct wall.

15. The improved support system of claim 14 wherein the fabricated integral cylinder and base member are varied in thickness from one region to another via smooth tapers and interconnecting radii to minimize thermal and mechanical stresses while maximizing mechanical stiffness.

16. The improved support system of claim 14 wherein a portion of the cylinder away from the integral base is fabricated separately and then joined to said base member for supporting said bosses and said pivoting hinge assembly.

17. The improved support system of claim 6 wherein said base member is fabricated to include regions of various thicknesses.

18. The improved support system of claim 7 wherein said base member includes a first base portion attached to the outer surface of the duct member and a second top portion joined to said base portion for supporting said pivoting hinge assembly.