Efficient anti-ice exhaust vent

• US 5,257,498 A
• Filed: 04/23/1992
• Issued: 11/02/1993
• Est. Priority Date: 04/23/1992
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Nikkanen, John P., Maier, Grant P., Bubello, Robert
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US07/872,575
• Time in Patent Office: 558 Days
• Field of Search: 60/39.093, 244/34 R, 244/34 B, 244/34 C
• US Class Current: 60/39.093
• CPC Class Codes: B64D 15/04 Hot gas application
• CPC Class Codes: B64D 2033/0233 comprising de-icing means
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An anti-icing system for a nacelle of a gas turbine powerplant is disclosed. Various construction details have been developed which provide means to exhaust fluid from an inlet shell cavity and into an external medium. In one embodiment, the exhaust means (62) includes a plurality of aerodynamically shaped vanes (66) disposed within the inlet shell cavity (52) and a plurality of exhaust slots (68) wherein each of the vanes is adjacent one of the exhaust slots. The vanes are adapted to turn a portion of the body of fluid flowing within the inlet shell cavity to a direction substantially normal to the direction of flow of the external medium.

Claims

1. A powerplant for an aircraft, the powerplant including a longitudinal axis, a nacelle disposed about the axis and defining an axial flowpath, the nacelle having an inner barrel defining a radially outer flow surface for a portion of the flowpath, an outer barrel disposed radially outward of the inner barrel and defining a flow surface for an external medium flowing over the nacelle, a forward bulkhead extending between the axially forward ends of the inner barrel and outer barrel, an annular inlet shell extending forward of the forward bulkhead, and an anti-ice system, wherein the anti-ice system includes:

a source of heating fluid, the source producing a fluid having a temperature and pressure greater than the temperature and pressure of the fluid medium external to the gas turbine engine;

a cavity bounded by the inlet shell and the forward bulkhead;

a conduit extending from the source to the cavity and defining a flowpath for heating fluid, the conduit having an outlet;

a nozzle disposed within the cavity and attached to the outlet of the conduit, the nozzle defining means to inject heating fluid into the cavity and to generate a body of fluid flowing within the cavity with a circumferentially directed component of velocity;

a plurality of exhaust slots disposed on the radially outer portion of the inlet shell;

a plurality of aerodynamically shaped exhaust vanes, each of the exhaust vanes disposed on the inlet shell, extending radially into the cavity, and being adjacent to and extending parallel to one of the plurality of exhaust slots, the exhaust vanes adapted to engage the fluid flowing within the cavity; and

wherein the plurality of exhaust vanes engage the fluid flowing within the cavity to turn a portion of the fluid to a direction substantially normal to the direction of flow of the medium external to the nacelle and to urge the portion of fluid to flow through the plurality of exhaust slots.

3. The anti-icing system according to claim 1, wherein the nacelle defines a fluid inlet for the powerplant, wherein the cavity is annular and disposed about the inlet, and wherein the injection means injects fluid such that the body of fluid flowing within the cavity flows with a circumferentially directed component of velocity.

4. The anti-icing system according to claim 3, wherein the exhaust means includes:

an exhaust slot disposed on the radially outer portion of the inlet shell, an aerodynamically shaped exhaust vane, the exhaust vane disposed on the inlet shell, extending radially into the cavity, and being adjacent to and extending parallel to the exhaust slot, the exhaust vane adapted to engage the body of fluid flowing within the cavity and to urge a portion of the fluid through the exhaust slot.

5. The anti-icing system according to claim 4, further comprising a fairing disposed upstream relative to the direction of flow of the body of fluid within the cavity, of the exhaust vane and adapted to block flow separation from occurring.

6. The anti-icing system according to claim 4, further comprising a fairing disposed downstream relative to the direction of flow of the body of fluid within the cavity, of the exhaust vane and adapted to block flow separation from occurring.

7. The anti-icing system according to claim 4, wherein the exhaust vane has a maximum thickness t, measured in the circumferential direction, and a rounded leading edge having a leading edge diameter d, and wherein the ratio d/t is between 0.4 and 0.6.

8. The anti-icing system according to claim 4, wherein the exhaust vane has a maximum thickness t, measured in the circumferential direction, and a length l, measured in the radial direction, and wherein the ratio t/l is between 0.3 and 0.5.

9. The anti-icing system according to claim 3, wherein the exhaust means further includes means to turn the portion of the fluid such that the fluid is ejected from the cavity in a direction forming an angle α

with the surface of the nacelle, the angle α

being greater than or equal to 60°

.

10. The anti-icing system according to claim 3, wherein the fluid being ejected has a blowing parameter β

, defined as the ratio of the magnitude of velocity of the ejected fluid to the magnitude of velocity of the external medium flowing over the nacelle, and wherein the exhaust means further includes means to eject fluid such that the blowing parameter β

is greater than or equal to 0.4

11. The anti-icing system according to claim 4, wherein the exhaust vane and exhaust slot extend in a direction normal to the direction of flow of the body of fluid within the cavity.

12. The anti-icing system according to claim 4, wherein the exhaust vane and exhaust slot provide means to eject the fluid in a radially outward direction.

2. An anti-icing system for a powerplant having a longitudinal axis, a source of heating fluid, and a nacelle defining a radially outer boundary for the power plant, the nacelle having a cavity disposed about the axis, the anti-icing system including:

means to flow heating fluid from the source to the cavity;

means to inject heating fluid into the cavity, the injection means injecting fluid such that a body of fluid flowing within the cavity is generated; and

means to exhaust fluid from the cavity into a medium external of the nacelle, the exhaust means engaging the fluid flowing within the cavity to turn a portion of the fluid to a direction substantially normal to the direction of flow of the medium external of the nacelle and to eject the fluid being exhausted at a flow velocity sufficient to penetrate the external medium.