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EP-4741645-A1 - BLEED VALVE SYSTEM FOR GAS TURBINE ENGINE

EP4741645A1EP 4741645 A1EP4741645 A1EP 4741645A1EP-4741645-A1

Abstract

A bleed valve system (80, 200, 300) for a gas turbine engine (10, 100, 100', 210, 240, 270), the bleed valve system (80, 200, 300) including a bleed valve (202, 202', 82, 222, 252, 262, 274, 310), a bleed valve exhaust duct (204, 304) fluidly connected to the bleed valve (202, 202', 82, 222, 252, 262, 274, 310), and a bleed valve exhaust nozzle (206, 306) fluidly connected to the bleed valve exhaust duct (204, 304), wherein the bleed valve exhaust duct (204, 304) and the bleed valve exhaust nozzle (206, 306) are fluidly separated from an exhaust nozzle of the gas turbine engine (10, 100, 100', 210, 240, 270) when the bleed valve system (80, 200, 300) is installed in the gas turbine engine (10, 100, 100', 210, 240, 270).

Inventors

  • BOWDEN, WILLIAM JOSEPH
  • Ostdiek, David Marion
  • McKnight, Ian
  • KHALID, SYED

Assignees

  • General Electric Company

Dates

Publication Date
20260513
Application Date
20251104

Claims (15)

  1. A bleed valve system (80, 200, 300) for a gas turbine engine (10, 100, 100', 210, 240, 270), the bleed valve system (80, 200, 300) comprising: a bleed valve (202, 202', 82, 222, 252, 262, 274, 310); a bleed valve exhaust duct (204, 304) fluidly connected to the bleed valve (202, 202', 82, 222, 252, 262, 274, 310); and a bleed valve exhaust nozzle (206, 306) fluidly connected to the bleed valve exhaust duct (204, 304), wherein the bleed valve exhaust duct (204, 304) and the bleed valve exhaust nozzle (206, 306) are fluidly separated from an exhaust nozzle of the gas turbine engine (10, 100, 100', 210, 240, 270) when the bleed valve system (80, 200, 300) is installed in the gas turbine engine (10, 100, 100', 210, 240, 270).
  2. The bleed valve system (80, 200, 300) of claim 1, wherein the gas turbine engine (10, 100, 100', 210, 240, 270) defines a radial direction, wherein the bleed valve exhaust nozzle (206, 306) is disposed outward in the radial direction from the exhaust nozzle when the bleed valve system (80, 200, 300) is installed in the gas turbine engine (10, 100, 100', 210, 240, 270).
  3. The bleed valve system (80, 200, 300) of claim 1, wherein the gas turbine engine (10, 100, 100', 210, 240, 270) defines a radial direction, wherein the bleed valve exhaust nozzle (206, 306) is disposed inward in the radial direction from the exhaust nozzle when the bleed valve system (80, 200, 300) is installed in the gas turbine engine (10, 100, 100', 210, 240, 270).
  4. The bleed valve system (80, 200, 300) of any one of the preceding claims, wherein the gas turbine engine (10, 100, 100', 210, 240, 270) includes an exhaust section (54) and the bleed valve exhaust nozzle (206, 306) is fluidly separated from the exhaust section (54) when the bleed valve system (80, 200, 300) is installed in the gas turbine engine (10, 100, 100', 210, 240, 270).
  5. The bleed valve system (80, 200, 300) of any one of the preceding claims, wherein the gas turbine engine (10, 100, 100', 210, 240, 270) includes a fan duct (172) including a fan exhaust nozzle (178), and the exhaust nozzle is the fan exhaust nozzle (178).
  6. The bleed valve system (80, 200, 300) of claim 5, wherein the gas turbine engine (10, 100, 100', 210, 240, 270) comprises a passage (194, 228, 258, 288), and wherein the bleed valve exhaust duct (204, 304) is fluidly connected to the fan duct (172) through the passage (194, 228, 258, 288) when the bleed valve system (80, 200, 300) is installed in the gas turbine engine (10, 100, 100', 210, 240, 270).
  7. The bleed valve system (80, 200, 300) of claim 6, further comprising a flow regulator (260) disposed in the passage (194, 228, 258, 288), the flow regulator (260) configured to allow air flow from the fan duct (172) to the bleed valve exhaust duct (204, 304) and to prevent air flow from the bleed valve exhaust duct (204, 304) to the fan duct (172).
  8. The bleed valve system (80, 200, 300) of claim 7, wherein the flow regulator (260) is one of a door (264) or a valve (262).
  9. The bleed valve system (80, 200, 300) of any one of the preceding claims, wherein the bleed valve exhaust nozzle (206, 306) extends aft of an exhaust section (54) of the gas turbine engine (10, 100, 100', 210, 240, 270).
  10. The bleed valve system (80, 200, 300) of any one of the preceding claims, wherein the bleed valve exhaust nozzle (206, 306) is fluidly isolated from the exhaust nozzle.
  11. The bleed valve system (80, 200, 300) of any one of the preceding claims, wherein the bleed valve exhaust duct (204, 304) includes a plurality of discrete ducts arranged circumferentially around the bleed valve exhaust nozzle (206, 306).
  12. A gas turbine engine (10, 100, 100', 210, 240, 270) defining a radial direction, the gas turbine engine (10, 100, 100', 210, 240, 270) comprising: a turbomachine (16, 120) including a turbomachine (16, 120) exhaust nozzle; a fan section (150) including a fan duct (172) and a fan exhaust nozzle (178); and a bleed valve system (80, 200, 300) comprising: a bleed valve (202, 202', 82, 222, 252, 262, 274, 310) fluidly connected to the turbomachine (16, 120); a bleed valve exhaust duct (204, 304) fluidly connected to the bleed valve (202, 202', 82, 222, 252, 262, 274, 310); and a bleed valve exhaust nozzle (206, 306) fluidly connected to the bleed valve exhaust duct (204, 304), wherein the bleed valve exhaust duct (204, 304) and the bleed valve exhaust nozzle (206, 306) are fluidly separated from the turbomachine (16, 120) exhaust nozzle and the fan exhaust nozzle (178).
  13. The gas turbine engine (10, 100, 100', 210, 240, 270) of claim 12, wherein the fan section (150) defines a bypass passage (194, 228, 258, 288), wherein the bleed valve exhaust duct (204, 304) and the bleed valve exhaust nozzle (206, 306) are fluidly separated from the bypass passage (194, 228, 258, 288).
  14. The gas turbine engine (10, 100, 100', 210, 240, 270) of any one of claims 12-13, wherein the bleed valve exhaust nozzle (206, 306) is disposed outward in the radial direction from the fan exhaust nozzle (178).
  15. The gas turbine engine (10, 100, 100', 210, 240, 270) of any one of claims 12-13, wherein the bleed valve exhaust nozzle (206, 306) is disposed inward in the radial direction from the fan exhaust nozzle (178).

Description

CROSS-REFERENCE TO RELATED APPLICATIONS This application is a non-provisional application claiming the benefit of priority under 35 U.S.C. § 119(e) to U.S. Provisional Application No. 63/718,311, filed November 8, 2024, which is hereby incorporated by reference in its entirety. FIELD The present disclosure relates to a bleed valve system for a gas turbine engine. BACKGROUND Gas turbine engines generally include a turbomachine, the turbomachine including, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air is provided to an inlet of the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section. Fuel is mixed with the compressed air and burned within the combustion section to provide combustion gases. The combustion gases are routed from the combustion section to the turbine section. The flow of combustion gases through the turbine section drives the turbine section and is then routed through the exhaust section, e.g., to atmosphere. BRIEF DESCRIPTION OF THE DRAWINGS A full and enabling disclosure of the present disclosure, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which: FIG. 1 is a schematic view of an exemplary gas turbine engine.FIG. 2 is a magnified view of the exemplary gas turbine engine of FIG. 1 illustrating a bleed valve system.FIG. 3 is a schematic view of another exemplary gas turbine engine.FIG. 4 is a magnified view of the exemplary gas turbine engine of FIG. 3 illustrating another bleed valve system.FIG. 5 is a magnified view of the exemplary gas turbine engine of FIG. 3 illustrating another bleed valve system.FIG. 6 is a schematic view of the exemplary gas turbine engine of FIG. 3 illustrating a passage connecting multiple streams.FIG. 7 is a schematic view of the exemplary gas turbine engine of FIG. 3 illustrating another passage connecting multiple streams.FIG. 8A is a magnified view of the passage of FIG. 7 illustrating a flow regulator.FIG. 8B is a magnified view of the passage of FIG. 7 illustrating another flow regulator.FIG. 9 is a schematic view of the exemplary gas turbine engine of FIG. 3 illustrating another passage connecting multiple streams.FIG. 10 is a perspective schematic view of a bleed valve system with a bleed valve exhaust duct including a plurality of discrete ducts.FIG. 11 is a top-down view of one of the discrete ducts of FIG. 10 along the line 11-11. DETAILED DESCRIPTION Reference will now be made in detail to present embodiments of the disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the disclosure. The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Additionally, unless specifically identified otherwise, all embodiments described herein should be considered exemplary. The singular forms "a", "an", and "the" include plural references unless the context clearly dictates otherwise. The term "at least one of" in the context of, e.g., "at least one of A, B, and C" refers to only A, only B, only C, or any combination of A, B, and C. An "exhaust nozzle" refers to any nozzle that exhausts gases from a gas turbine engine, such as a fan exhaust nozzle or a turbomachine exhaust nozzle. The terms "upstream" and "downstream" refer to the relative direction with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction from which fluid flows, and "downstream" refers to the direction to which the fluid flows. In this context, a "nozzle" is an opening or structure that directs air flow away from a gas turbine engine with at least some thrust output. In general, a nozzle outputs air flow substantially parallel to a direction of flight. The present disclosure is generally related to operation of a turbomachine of a gas turbine engine. Booster and compressor architectures for improved performance may require the booster to have a portion of the flow bled at low power conditions, such as idle. This flow is called "variable bleed valve" (VBV) or "bleed valve" flow. Gas turbine engines can exhaust VBV flow into an alternate turbomachinery exhaust stream, such as the fan stream or bypass stream for ducted turbofans. Such exhausting can create various integration challenges. In some forms, exhausting the VBV flow into an alternate exhaust stream reduces turbomachinery operability, increases acoustics, or increases engine weight. For example, exhausting VBV flow into