Exhaust nozzle for suppressing infrared radiation

• US 5,992,140 A
• Filed: 06/24/1997
• Issued: 11/30/1999
• Est. Priority Date: 06/24/1997
• Status: Expired due to Term

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Presz, Walter M. Jr., Hammond, Mark H.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US08/881,344
• Time in Patent Office: 889 Days
• Field of Search: 20/39.5, 20/262, 20/266, 239/265.17
• US Class Current: 60/262
• CPC Class Codes: B33Y 80/00 Products made by additive manufacturing
• CPC Class Codes: B64D 2033/045 comprising infrared suppressors
• CPC Class Codes: B64D 33/04 of exhaust outlets or jet pipes exhaust outlets for combustion engines in general F01N; jet pipes or nozzles for jet-propulsion plants per se F02K; plants characterised by the form or arrangement of the jet pipe or nozzle F02K ; attitude, flight direction, or altitude control by jet reaction B64C
• 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: F02K 1/825 Infrared radiation suppressors
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An exhaust nozzle (24 or 28) operative to suppress the InfraRed (IR) signature radiated from the high-temperature exhaust of an engine (12) which exhaust nozzle (24 or 28) includes an inlet conduit adapted for receiving the high-temperature engine exhaust and a plurality of adjoined lobes (30) integrally formed in combination with the inlet conduit. The adjoined lobes (30) are characterized by a first and second plurality of penetrating lobes (60, 62 or 70, 72) which are adapted for admixing low-temperature gaseous fluid with the high-temperature exhaust and which are axially staggered with respect to each other. In the preferred embodiment, at least one of said plurality of penetrating lobes (60 or 62, 70 or 72) extends into a core region (CR) of the exhaust nozzle (24 or 28) to effect thorough mixing of the engine exhaust with the low temperature gaseous fluid. Various embodiments of such exhaust nozzle (24 or 28) are described in the context of a multi-stage mixer/ejector (20).

Claims

1. An exhaust nozzle (28) operative to suppress the infrared signature radiated from the high-temperature exhaust of an engine (12) including:

an inlet conduit (46) adapted for receiving a primary flow PF of high-temperature engine exhaust;

a plurality of adjoined lobes (30) integrally formed in combination with said inlet conduit (46) and defining an outlet end of the exhaust nozzle (28), each of said adjoined lobes (30) being substantially perpendicular with respect midplane P_M defined by said outlet end, said adjoined lobes (30), furthermore, being adapted for admixing a secondary flow SF of low-temperature gaseous fluid with said primary flow PF of high-temperature exhaust,

said engine exhaust nozzle (28) being further characterized by;

said adjoined lobes (30) defining a first and second plurality of penetrating lobes (70,

     72), said penetrating lobes (70,

     72) each defining an external flow trough (30_EFT), said external flow troughs (30_EFT) of said first plurality (70) defining a core region (CR);

said penetrating lobes (70,

     72) furthermore being inset with respect to each other; and

said second plurality of penetrating lobes (72) projecting axially downstream of said first plurality of penetrating lobes (70) and extending into said core region (CR) so as to direct the secondary flow SF of low temperature gaseous fluid deeply into the primary flow PF of high temperature engine exhaust.

2. The exhaust nozzle (28) according to claim 1 wherein the exhaust nozzle (28) is also operative to suppress the infrared signature radiated from the hot metal components of the engine (12), and wherein said penetrating lobes (70,72) define a plurality of turning vanes (80) adapted for redirecting the primary exhaust flow PF.

3. The exhaust nozzle (28) according to claim 1 wherein first plurality of penetrating lobes (70) define an exit plane P₇₀, and wherein said first and second plurality of penetrating lobes (70, 72) are inset at an axial location (74) inboard of said exit plane (P₇₀) for preventing direct line-of-sight viewing into said exhaust nozzle (28).

4. The exhaust nozzle (28) according to claim 1 wherein said inlet conduit (46) defines a substantially circular geometric profile and said penetrating lobes (70, 72) define a substantially rectangular geometric profile.

5. The exhaust nozzle (28) according to claim 1 wherein said second plurality of penetrating lobes define an exit plane P₇₂, and wherein said second plurality of penetrating lobes (72) fully traverse said core region (CR) so as to divide the primary flow into a plurality of discrete flow segments.