Compressor discharge flowpath

• US 5,165,850 A
• Filed: 07/15/1991
• Issued: 11/24/1992
• Est. Priority Date: 07/15/1991
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Barron, Michael L., Humke, Brian J., Wakeman, Thomas G., Bellia, Donald L., Baehre, Eric E.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Mattingly, Todd
• Application Number:
  US07/729,956
• Time in Patent Office: 498 Days
• Field of Search: 415/134, 415/135, 415/139, 415/182.1, 415/208.1, 415/208.2, 415/209.2, 415/210.1, 415/211.2, 415/213.1
• US Class Current: 415/209.2
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F04D 29/541 Specially adapted for elastic fluid pumps F04D29/56 takes precedence
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means

Abstract

A compressor discharge flowpath for a gas turbine engine includes flowpath outer and inner walls joined to a plurality of circumferentially spaced flowpath dividers extending therebetween. An inner support extends from the inner wall and is joined to a turbine nozzle, and an outer support extends from the outer wall and is joined to an engine casing. The outer support preferably includes a plurality of circumferentially spaced beams being sized and configured for carrying both axial force and torque transmitted therethrough from the turbine nozzle to the casing while allowing the beams to bend radially for accommodating differential thermal movement between the casing and the outer wall.

Claims

1. For a gas turbine engine having an axial centerline axis, a compressor for discharging compressed airflow, a combustor for receiving said compressed airflow and generating combustion gases, a turbine nozzle for receiving said combustion gases, and a casing surrounding said compressor, combustor, and nozzle, an annular compressor discharge flowpath for channeling said compressed airflow from said compressor to said combustor comprising:

a flowpath outer wall;

a flowpath inner wall spaced from said outer wall;

a plurality of circumferentially spaced radially extending flowpath dividers extending between and fixedly joined to said outer and inner walls, each of said dividers having a longitudinal axis;

an annular inner support fixedly joined to said inner wall and extending axially for being joined to said turbine nozzle;

an outer support fixedly joined to said casing and extending axially for being joined to said outer wall, and comprising a plurality of circumferentially spaced beams each having a length along a longitudinal axis, said beams being sized and configured for carrying both axial force and torque transmitted therethrough from said nozzle to said casing while allowing said beams to bend radially for accommodating differential thermal movement between said casing and said outer wall; and

said beams being configured in symmetric paris, with each beam pair being disposed adjacent to and straddling a respective one of said dividers, with said longitudinal axes of said beam pair being equally spaced circumferentially oppositely to said longitudinal axis of said straddled divider.

2. A compressor discharge flowpath according to claim 1 wherein said beam pair longitudinal axes intersect each other at an acute angle.

3. A compressor discharge flowpath according to claim 2 wherein said beam longitudinal axes are disposed substantially parallel to said engine centerline axis for providing radial flexibility to accommodate said differential thermal movement.

4. A compressor discharge flowpath according to claim 3 wherein each of said beams includes a width and a thickness, said thickness being less than said width for providing radial flexibility to accommodate said differential thermal movement.

5. A compressor discharge flowpath according to claim 4 in the form of a diffuser, wherein said flowpath dividers are struts therein.

6. For a gas turbine engine having an axial centerline axis, a compressor for discharging compressed airflow, a combustor for receiving said compressed airflow and generating combustion gases, a turbine nozzle for receiving said combustion gases, and a casing surrounding said compressor, combustor, and nozzle, an annular compressor discharge flowpath for channeling said compressed airflow from said compressor to said combustor comprising:

a flowpath outer wall;

a flowpath inner wall spaced from said outer wall;

a plurality of circumferentially spaced radially extending flowpath dividers extending between and fixedly joined to said outer and inner walls;

an annular inner support fixedly joined to said inner wall and extending axially for being joined to said turbine nozzle;

an outer support fixedly joined to said casing and extending axially for being joined to said outer wall, and comprising a plurality of circumferentially spaced beams each having a length along a longitudinal axis, said beams being sized and configured for carrying both axial force and torque transmitted therethrough from said nozzle to said casing while allowing said beams to bend radially for accommodating differential thermal movement between said casing and said outer wall; and

each of said flowpath dividers including an extension extending radially outwardly from said outer wall and fixedly joined to a respective one of said beams for channeling said axial force from said nozzle through said dividers and beams to said casing.

7. A compressor discharge flowpath according to claim 6 wherein each of said beams has a width being greater than a width of said respective divider.

8. A compressor discharge flowpath according to claim 7 wherein said beam includes a beam transition fixedly joining said beam to said respective divider extension, said beam transition having a width decreasing from said beam width to said divider width and a thickness increasing from said beam to said divider extension.

9. A compressor discharge flowpath according to claim 8 wherein each of said beams includes a thickness being less than said beam width for providing radial flexibility to accommodate said differential thermal movement.

10. A compressor discharge flowpath according to claim 9 wherein said beam longitudinal axis is disposed at an angle relative to said engine centerline axis up to about 45°

for providing radial flexibility to accommodate said differential thermal movement.

11. A compressor discharge flowpath according to claim 10 in the form of a diffuser wherein said flowpath dividers ar struts therein.

12. A compressor discharge flowpath according to claim 10 wherein said flow dividers are outlet guide vanes.

13. A compressor discharge flowpath according to claim 10 wherein each of said beams is disposed adjacent to a respective one of said dividers with said beam longitudinal axis being axially aligned with a longitudinal axis of said divider.