Accessory for a turbine engine

{
  "publication_number": "US4238092A",
  "country": "US",
  "kind": "A",
  "title": "Accessory for a turbine engine",
  "abstract": "An accessory for a jet engine for tuning turbine exhaust gases for maximum thrust capabilities in the absence of a turbine thrust reverser and cowling combination normally for and utilized thereon. The accessory comprises an inner streamlined nozzle shell forming a continuation of the outer skin of the turbine exhaust duct, a center mounted engine plug providing a path for the turbine gases between the inner nozzle surface and the engine plug outer surface and a transition adapter for mating and attaching the plug to the center of the engine. The engine plug is further provided with an opening between its engine attached and outer ends providing communication between the engine and the atmosphere adjacent the rear end of the plug. The accessory further comprises a fairing for attachment to the pylon supporting the engine to further tune the gases leaving the nozzle.",
  "claims": [
    "1. A thrust tuning accessory for use with a turbine engine pylon mounted to an aircraft having a turbine exhaust duct utilizing said accessory in the absence of a thrust reverser thereon comprising: an outer cowl member having streamlined inner and outer surfaces attached to the outer periphery of the turbine exhaust duct forming a rearward streamlined continuation thereof; a hollow open ended engine center plug having an outer surface form defining a thrust gas path with the inner surface of said cowl member, said plug having a longitudinal cross-sectional profile resembling two abutting frustroconic sections, the open end of said engine plug remote from said engine being substantially pointed and extending further rearward than said outer cowl member; and a transition means for attaching said engine center plug to said engine, said engine accessory further comprising a fairing element for attachment to said pylon wherein the configuration of the outer surface of said fairing element cooperates with the outer boundary of the engine gas to further tune the gases leaving said engine and wherein said fairing element is substantially \"V\" shaped in vertical cross-section with the downward extending closed end surface of the \"V\" being substantially flattened with the side surfaces of the \"V\" substantially conforming with the outer surface of said pylon and the substantially flattened portion slightly convex with respect to said pylon to substantially match the shape of the outer periphery of the exhaust gases exiting from the nozzle.",
    "2. A thrust tuning accessory for use with a turbine engine pylon mounted to an aircraft having a turbine exhaust duct utilizing said accessory in the absence of a thrust reverser thereon comprising: an outer cowl member having streamlined inner and outer surfaces attached to the outer periphery of the turbine exhaust duct forming a rearward streamlined continuation thereof; a hollow center plug open at opposite ends to provide a through passageway and having an outer surface form defining a thrust gas path, said plug having a longitudinal cross-sectional profile resembling two axially aligned abutting frustro-conic sections, the end of said engine plug remote from said engine being substantially pointed and extending further rearward than said outer cowl member; a transition means for attaching said engine center plug to said engine; and a fairing element for attachment to said pylon to further tune the tuned gases leaving said engine, said fairing element is substantially \"V\" shaped in vertical cross-section with the downward extending closed end of the \"V\" substantially flattened with the side surfaces of the \"V\" conforming substantially with the outer surface of said pylon and the substantially flattened portion slightly curved inward in a convex manner with respect to said pylon adjacent surface away from said thrust gas path to substantially match the outer periphery of the exhaust gases exiting from the nozzle."
  ],
  "description_excerpt": "This is a continuation of Ser. No. 815,690, filed July 17, 1977 now abandoned.\n\nThe invention pertains to engine nozzle and plug and more particularly to an engine nozzle, plug and pylon fairing to be utilized on the engine in place of a turbine thrust reverser normally provided therewith.\n\nIt is well known that since the original concept of jet engines for aircraft, fan type or otherwise, stopping of the aircraft is a considerable problem due to the operating speeds required both for take off and landings. This problem has increased due to the size and weight of modern aircraft utilizing this type of propulsion. Wheel brakes, fan reverser and thrust reverser have been used both singularly and in various combinations. Safety laws of the United States require that an aircraft be rated for take off and landing distances according to their ability to brake with wheel brakes alone and reversers of both types are normally added only to further increase the safety margin of the aircraft.\n\nAircraft engines designed to include reversers will not operate efficiently when the reverser units are removed. An example of this type of engine design is the General Electric engine utilized on the Douglas DC-10. aircraft. On this specific aircraft, the turbine thrust reverser provides only 5% to 8% of the aircraft braking capabilities and weighs in excess of 500 pounds each unit. Obviously, an aircraft of this type would have increased performance if the reversers could be physically removed to reduce overall aircraft weight while maintaining or improving the engine's overall efficiency.",
  "cpc": [
    "F02K 1/00",
    "B64D 29/02",
    "B64D 33/04",
    "F02K 1/04",
    "Y02T 50/60"
  ],
  "ipc": [
    "F02K 1/00",
    "F02K 1/04"
  ],
  "assignees": [
    "Rohr Industries Inc"
  ],
  "inventors": [
    "John M. Brennan"
  ],
  "filing_date": "1978-08-17",
  "publication_date": "1980-12-09",
  "grant_date": "1980-12-09",
  "priority_date": "1978-08-17",
  "application_number": "US-93466078-A",
  "family_id": "25465877",
  "cited_by_count": 44,
  "citations": [
    "US3027713A",
    "US4044555A",
    "US3423048A",
    "US3799476A",
    "GB1417504A"
  ]
}