US-12618376-B2 - Bleeding core air from a turbine engine core flowpath

Abstract

A bleed system for a turbine engine includes a bleed port, an inlet passage, an outlet passage, a cavity and a flow diverter. The bleed port is disposed longitudinally along a core flowpath between an inlet into the core flowpath and an exhaust from the core flowpath. The bleed port fluidly couples the core flowpath to the inlet passage. The flow diverter is configured to move between a first position and a second position. When the flow diverter is in the first position, the flow diverter fluidly decouples the inlet passage from the outlet passage, and the cavity is fluidly coupled with the inlet passage and is downstream of the flow diverter. When the flow diverter is in the second position, the flow diverter fluidly couples the inlet passage to the outlet passage.

Inventors

• Matthew R. Feulner
• Daniel B. Kupratis

Assignees

• RTX CORPORATION

Dates

Publication Date

20260505

Application Date

20240813

Claims (18)

1. 1 . An assembly of a turbine engine, comprising: an engine core including a core flowpath, a compressor section, a combustor section and a turbine section, the core flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath; and a bleed system including a bleed port, an inlet passage, an outlet passage, a cavity and a valve element, the bleed port disposed longitudinally along the core flowpath between the inlet into the core flowpath and the exhaust from the core flowpath, the bleed port fluidly coupling the core flowpath to the inlet passage, and the valve element moves between a first position and a second position; wherein, when the valve element is in the first position, the valve element fluidly decouples the inlet passage from the outlet passage, and the cavity is fluidly coupled with the inlet passage and is downstream of the valve element; and wherein, when the valve element is in the second position, the valve element fluidly couples the inlet passage to the outlet passage; wherein the engine core extends along a centerline axis; and wherein the valve element moves axially along the centerline axis between the first position and the second position.
2. 2 . The assembly of claim 1 , wherein the bleed port is disposed longitudinally along the core flowpath downstream of the compressor section.
3. 3 . The assembly of claim 1 , wherein the bleed port is disposed longitudinally along the core flowpath within the compressor section.
4. 4 . The assembly of claim 1 , wherein, when the valve element is in the second position, the cavity is fluidly coupled to at least one of the inlet passage and the outlet passage.
5. 5 . The assembly of claim 1 , wherein, when the valve element is in the second position, the valve element fluidly decouples the cavity from the inlet passage.
6. 6 . The assembly of claim 1 , wherein the bleed system directs debris traveling within the core flowpath through the bleed port and into the inlet passage; and the valve element directs the debris from the inlet passage into the cavity when the valve element is in the first position.
7. 7 . The assembly of claim 6 , wherein the bleed system directs the debris from the inlet passage into the outlet passage when the valve element is in the second position.
8. 8 . The assembly of claim 7 , wherein, when the valve element is in the second position, the bleed system directs the debris out of the engine core through the outlet passage.
9. 9 . The assembly of claim 1 , wherein the turbine engine comprises a turbofan engine, and the assembly further comprises: a bypass flowpath outside of the engine core; and the outlet passage couples the inlet passage to the bypass flowpath when the valve element is in the second position.
10. 10 . The assembly of claim 1 , wherein the valve element at least partially forms a cavity inlet into the cavity when the valve element is in the first position.
11. 11 . The assembly of claim 1 , wherein the cavity is a blind cavity.
12. 12 . The assembly of claim 1 , wherein the bleed system further includes a second outlet passage; and when the valve element is in a third position, the valve element fluidly couples the inlet passage to the cavity and fluidly couples the cavity to the second outlet passage.
13. 13 . The assembly of claim 12 , wherein, when the valve element is in the third position, the valve element fluidly couples the inlet passage to the outlet passage.
14. 14 . The assembly of claim 12 , wherein, when the valve element is in the first position, the valve element fluidly decouples the cavity from the second outlet passage.
15. 15 . The assembly of claim 12 , wherein, when the valve element is in the second position, the valve element fluidly decouples the cavity from the second outlet passage.
16. 16 . The assembly of claim 1 , the cavity is located axially along the centerline axis between the inlet into the core flowpath and the inlet passage.
17. 17 . The assembly of claim 1 , the inlet passage is located axially along the centerline axis between the inlet into the core flowpath and the cavity.
18. 18 . An assembly of a turbine engine, comprising: an engine core including a core flowpath, a compressor section, a combustor section and a turbine section, the core flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath; and a bleed system including a bleed port, an inlet passage, an outlet passage, a cavity and a valve element, the bleed port disposed longitudinally along the core flowpath between the inlet into the core flowpath and the exhaust from the core flowpath, the bleed port fluidly coupling the core flowpath to the inlet passage, and the valve element moves between a first position and a second position; wherein, when the valve element, is in the first position, the valve element, fluidly decouples the inlet passage from the outlet passage, the cavity is fluidly coupled with the inlet passage through a cavity inlet, and the valve element, at least partially forms the cavity inlet; and wherein, when the valve element, is in the second position, the valve element, fluidly couples the inlet passage to the outlet passage; and wherein the cavity provides a Helmholtz resonator.

Description

BACKGROUND OF THE DISCLOSURE 1. Technical Field This disclosure relates generally to an aircraft and, more particularly, to bleeding air from a flowpath of an aircraft engine. 2. Background Information Various systems and methods are known in the art for bleeding air from a flowpath of an aircraft engine. While these known systems and methods have various benefits, there is still room in the art for improvement. SUMMARY OF THE DISCLOSURE According to an aspect of the present disclosure, an assembly is provided for a turbine engine. This assembly includes an engine core and a bleed system. The engine core includes a core flowpath, a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The bleed system includes a bleed port, an inlet passage, an outlet passage, a cavity and a flow diverter. The bleed port is disposed longitudinally along the core flowpath between the inlet into the core flowpath and the exhaust from the core flowpath. The bleed port fluidly couples the core flowpath to the inlet passage. The flow diverter is configured to move between a first position and a second position. When the flow diverter is in the first position, the flow diverter fluidly decouples the inlet passage from the outlet passage, and the cavity is fluidly coupled with the inlet passage and is downstream of the flow diverter. When the flow diverter is in the second position, the flow diverter fluidly couples the inlet passage to the outlet passage. According to another aspect of the present disclosure, another assembly is provided for a turbine engine. This assembly includes an engine core and a bleed system. The engine core includes a core flowpath, a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The bleed system includes a bleed port, an inlet passage, an outlet passage, a cavity and a flow diverter. The bleed port is disposed longitudinally along the core flowpath between the inlet into the core flowpath and the exhaust from the core flowpath. The bleed port fluidly couples the core flowpath to the inlet passage. The flow diverter is configured to move between a first position and a second position. When the flow diverter is in the first position, the flow diverter fluidly decouples the inlet passage from the outlet passage, the cavity is fluidly coupled with the inlet passage through a cavity inlet, and the flow diverter at least partially forms the cavity inlet. When the flow diverter is in the second position, the flow diverter fluidly couples the inlet passage to the outlet passage. According to still another aspect of the present disclosure, another assembly is provided for a turbine engine. This assembly includes an engine core and a bleed system. The engine core includes a core flowpath, a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The bleed system includes a bleed port, an inlet passage, a first outlet passage, a second outlet passage, a cavity and a flow diverter. The bleed port is disposed longitudinally along the core flowpath. The bleed port fluidly couples the core flowpath to the inlet passage. The flow diverter is configured to move between a first position and a second position. When the flow diverter is in the first position, the flow diverter fluidly decouples the inlet passage from the first outlet passage and fluidly couples the inlet passage to the cavity. When the flow diverter is in the second position, the flow diverter fluidly couples the inlet passage to the first outlet passage and fluidly decouples the inlet passage from the cavity. When the flow diverter is in a third position between the first position and the second position, the flow diverter fluidly couples the inlet passage to the first outlet passage and the cavity, and the flow diverter fluidly couples the cavity to the second outlet passage. The bleed port may be disposed longitudinally along the core flowpath downstream of the compressor section. The bleed port may be disposed longitudinally along the core flowpath downstream within the compressor section. When the flow diverter is in the second position, the cavity may be fluidly coupled to at least one of the inlet passage and the outlet passage. When the flow diverter is in the second position, the flow diverter may fluidly decouple the cavity from the inlet passage. The bleed system may be configured to direct debris traveling within the core flowpath through the bleed port and into the inlet passage. The f