Gas turbine nozzles

• US 4,813,230 A
• Filed: 09/22/1987
• Issued: 03/21/1989
• Est. Priority Date: 08/26/1987
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Braithwaite, Anthony
• Primary Examiner(s): Stout, Donald E.
• Application Number:
  US07/099,873
• Time in Patent Office: 546 Days
• Field of Search: 60/262, 60/263, 60/264, 60/271, 181/220, 239/265.17, 239/127.3, 29/157 C
• US Class Current: 60/262
• CPC Class Codes: F02K 1/386 mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
• CPC Class Codes: Y10T 29/49234 Rotary or radial engine making
• CPC Class Codes: Y10T 29/49432 Nozzle making

Abstract

A bypass gas turbine has a mixer nozzle at the turbine outlet with a main body, of lobed cross-section to promote mixing of the turbine gas flow and the bypass flow. For a transition at the forward end of the nozzle from the essentially circular boundary between the two flows preceding the turbine outlet to said lobed form, there is an annular connecting ring fairing a channel section with radially inner and outer flanges to which the forward end of the fabricated main body is secured at the peaks and troughs of its lobes. Fairing elements are secured to the flanges to blend with the lobed form of the nozzle body. Because the nozzle body has a lobed form along its entire length it can be constructed as a single skin fabrication while retaining sufficient stiffness to prevent unacceptable deformations from the pressure forces on it under reverse thrust conditions.

Claims

1. A bypass gas turbine engine having a hot gas exhaust outlet for exit gas flows from turbine passages and a bypass passage in which an inner mixer nozzle is located for mixing the exit gas flows from the turbine passages and from a bypass passage surrounding the turbine passages, the turbine and bypass passages being separated by an essentially annular boundary wall, the mixer nozzle having a lobed configuration to promote mixing of the gas flows and, along its length, providing a progressive transition from said annular boundary wall to said lobed configuration, the mixer nozzle comprising a main body formed by a single skin fabrication having said lobed configuration extending over its length with the depth of the lobes increasing from a relatively shallow form at its forward end, said nozzle body being mounted onto the turbine outlet through an annular connecting member having radially spaced inner and outer faces, said forward end of said main body having circumferentially alternating inner and outer portions with the said inner portions being secured to said inner face of said annular connecting member and said outer portions of said main body being secured to said outer face of said annular connecting member, and fairing means between said connection member and the nozzle body providing a transition between said annular boundary wall at the entry end of the nozzle and the lobed configuration of said nozzle body further downstream.

2. An engine according to claim 1 wherein the connecting member comprises a channel section with respective annular flanges providing said inner and outer faces.

3. An engine according to claim 2 wherein at said forward end of said nozzle body the cross-sectional form of said lobed configuration provides radially inner and outer lands conforming to the radii of said inner and outer faces of the annular connecting member and through which the nozzle body is secured to the annular connecting member.

4. An engine according to any one of claims 1 to 3 wherein said fairing means comprise members extending in cantilever manner from the connecting member inner and outer faces.

5. An engine according to claim 4 wherein hard metal facings are provided on areas of the fairing means rearwards of the connecting member inner and outer faces in contact with adjoining surfaces of the nozzle.

6. An engine according to claims 1, 2 or 3 wherein the individual lobes of the nozzle are provided with separate fairing elements.

7. An engine according to claim 6 wherein on the inner face of the nozzle, at least some of said fairing elements overlap each other.

8. An engine according to claim 6 wherein at least one of said connecting member inner and outer faces is overlapped by a rearmost portion of said boundary wall and the fairing elements are spaced from each other on said at least one face.

9. An engine according to claims 1, 2 or 3 wherein the nozzle body is composed of sheet-metal pressings welded together with junctions that extent longitudinally of the nozzle at or adjacent the outer diameter of its lobes.

10. An engine according to claims 1, 2 or 3 wherein the nozzle body is composed of sheet metal pressings welded together at a circumferential junction intermediate the length of the nozzle.