Bloom mixer for a turbofan engine

• US 6,578,355 B1
• Filed: 04/09/2001
• Issued: 06/17/2003
• Est. Priority Date: 03/05/1999
• Status: Expired due to Term

• Current Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Inventors: Mundt, Christian
• Primary Examiner(s): Kim, Ted
• Application Number:
  US09/623,739
• Time in Patent Office: 799 Days
• Field of Search: 602/62, 602/64, 239/265.17, 239/265.19, 181/213, 181/220
• 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: F02K 1/48 Corrugated nozzles
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention relates to lobe-type mixer tube for a bypass jet engine in which a bypass flow delivered by a fan is mixed with a hot gas stream issuing from the core engine, said lobe-type mixer tube having essentially circumferentially equally spaced gutter-shaped, radially moderately alternately inward and outward directed ducts to guide both the bypass flow and the hot gas stream, said ducts each having an end formed by an essentially plane extreme section and the respective extreme sections of some ducts when viewed in a longitudinal section extending in the direction of flow being inclined vis-a-vis the extreme sections of the other ducts. In this arrangement the radially outward directed ducts, when viewed circumferentially, alternately issue at points offset one from the other. In a preferred aspect, every other of the moderately radially outward directed ducts, when viewed circumferentially, has an extreme section which extends essentially normal to the centerline of the lobe-type mixer tube, while the extreme sections of the intervening moderately radially outward directed ducts are inclined counter the direction of flow and are therefore scarfed inversely.

Claims

1. A lobe-type mixer tube for a bypass jet engine in which a bypass flow delivered by a fan is mixed with a hot gas stream issuing from a core engine, said lobe-type mixer having essentially circumferentially equally spaced gutter-shaped, radially inward and outward directed ducts to guide both the bypass flow and the hot gas stream, said ducts each having an end formed by an essentially plane extreme section and the respective extreme sections of some ducts when viewed in a longitudinal section extending in a direction of flow being inclined vis-à

-vis the extreme sections of the other ducts, so that the various ducts when viewed in the direction of flow issue at various points offset one from the other, wherein alternate ones of the radially outward directed ducts when viewed in the circumferential direction issue at points that are axially offset from each other in the direction of flow.

2. The lobe-type mixer tube in accordance with claim 1, wherein, when viewed in the circumferential direction, every other radially outward directed duct has an extreme section which extends essentially normal to a centerline of the lobe-type mixer or is inclined in the direction of flow, while the extreme sections of the intervening radially outward directed ducts are inclined counter to the direction of flow and these ducts accordingly are inversely scarfed.

3. The lobe-type mixer tube of claim 2, wherein lateral walls of the gutter-shaped ducts essentially lie in radial planes extending through the centerline of the lobe-type mixer tube, with the lateral walls of each duct running in parallel with each other.

4. The lobe-type mixer tube of claim 1, wherein lateral walls of the gutter-shaped ducts essentially lie in radial planes extending through the centerline of the lobe-type mixer tube, with the lateral walls of each duct running in parallel with each other.

5. A lobe-type mixer tube for a bypass jet engine in which a bypass flow delivered by a fan is mixed with a hot gas stream issuing from a core engine, said lobe-type mixer tube having essentially circumferentially equally spaced gutter-shaped, radially alternately inward and outward directed ducts to guide both the bypass flow and the hot gas stream, said ducts each having an end formed by an essentially plane extreme section and the respective extreme sections of adjacent ducts when viewed in a longitudinal section extending in a direction of flow being inclined relative to each other, so that the various ducts when viewed in the direction of flow issue at various points offset one from the other, wherein four each circumferentially successive ducts form a group that repeats over the entire circumference and consists of a pair of radially outward directed ducts and a pair of radially inward directed ducts, one each duct of a pair being shorter and the other duct of the pair being longer than the other, where when viewed circumferentially, a longer inward directed duct is followed by a longer outward directed duct, which is followed by a shorter inward directed duct which in turn is followed by a shorter outward directed duct.

6. The lobe-type mixer tube of claim 5, wherein the longer inward directed duct is heavily scarfed, while the shorter inward directed duct is little or not scarfed.

7. The lobe-type mixer tube of claim 6, wherein the shorter outward directed duct is inversely scarfed.

8. The lobe-type mixer tube of claim 7, wherein the group repeats at least one of periodically and axis-symmetrically over the circumference.

9. The lobe-type mixer tube of claim 6, wherein the group repeats at least one of periodically and axis-symmetrically over the circumference.

10. The lobe-type mixer tube of claim 5, wherein the shorter outward directed duct is inversely scarfed.

11. The lobe-type mixer tube of claim 10, wherein the group repeats at least one of periodically and axis-symmetrically over the circumference.

12. The lobe-type mixer tube of claim 5, wherein the group repeats at least one of periodically and axis-symmetrically over the circumference.