US-12623785-B2 - Open rotor propulsion system with exhaust mixer(s)

Abstract

An aircraft propulsion system includes a propulsion section and a turbine engine. The propulsion section includes an open propulsor rotor and an open guide vane structure disposed next to the open propulsor rotor. The turbine engine is configured to drive rotation of the open propulsor rotor. The turbine engine includes an engine core, an inlet section, an exhaust section and a flowpath. The engine core includes a compressor section, a combustor section and a turbine section. The inlet section includes a flowpath inlet. The exhaust section includes a flowpath exhaust and a mixer at the flowpath exhaust. The flowpath extends from the flowpath inlet, through the inlet section, the compressor section, the combustor section, the turbine section and the exhaust section, to the flowpath exhaust. The mixer is configured to mix combustion products exhausted from the flowpath through the flowpath exhaust with ambient air outside of the propulsion system.

Inventors

• Jon E. Sobanski
• Jeffrey T. Morton
• Andrew E. Breault

Assignees

• RTX CORPORATION

Dates

Publication Date

20260512

Application Date

20241001

Claims (14)

1. 1 . A propulsion system for an aircraft, comprising: a propulsion section including an open propulsor rotor and an open guide vane structure disposed next to the open propulsor rotor; and a turbine engine configured to drive rotation of the open propulsor rotor about an axis, the turbine engine including an engine core, an inlet section, an exhaust section and a flowpath, the engine core including a compressor section, a combustor section and a turbine section, the inlet section comprising a flowpath inlet, the exhaust section comprising a flowpath exhaust and a mixer at the flowpath exhaust, and the flowpath extending from the flowpath inlet, through the inlet section, the compressor section, the combustor section, the turbine section and the exhaust section, to the flowpath exhaust; wherein the mixer is configured to mix combustion products exhausted from the flowpath through the flowpath exhaust with ambient air outside of the propulsion system; wherein the flowpath exhaust is formed collectively by a plurality of exhaust outlets; and wherein the mixer is one of a plurality of mixers, and each of the plurality of mixers is configured with a respective one of the plurality of exhaust outlets.
2. 2 . The propulsion system of claim 1 , wherein a first of the plurality of mixers comprises a chevron mixer.
3. 3 . The propulsion system of claim 1 , wherein a first of the plurality of mixers comprises a serrated edge mixer.
4. 4 . The propulsion system of claim 1 , wherein the flowpath exhaust comprises a first exhaust outlet of the plurality of exhaust outlets; and a first of the plurality of mixers forms an outer peripheral boundary of the first exhaust outlet.
5. 5 . The propulsion system of claim 1 , wherein the flowpath exhaust comprises a first exhaust outlet of the plurality of exhaust outlets; and a first of the plurality of mixers includes a plurality of mixer projections arranged circumferentially about the first exhaust outlet.
6. 6 . The propulsion system of claim 5 , wherein the plurality of mixer projections comprises a plurality of chevrons.
7. 7 . The propulsion system of claim 5 , wherein the plurality of mixer projections are symmetrically arranged circumferentially about the first exhaust outlet.
8. 8 . The propulsion system of claim 5 , wherein the exhaust outlet is non-annular.
9. 9 . The propulsion system of claim 1 , wherein the flowpath exhaust is disposed axially between the open propulsor rotor and the open guide vane structure.
10. 10 . The propulsion system of claim 1 , wherein the open guide vane structure is disposed axially between the open propulsor rotor and the flowpath exhaust.
11. 11 . The propulsion system of claim 1 , wherein the turbine section is disposed axially between the compressor section and the open propulsor rotor.
12. 12 . The propulsion system of claim 1 , wherein the flowpath exhaust is axially aligned with the open guide vane structure.
13. 13 . A propulsion system for an aircraft, comprising: a propulsion section including an open propulsor rotor and an open guide vane structure disposed next to the open propulsor rotor; and a turbine engine configured to drive rotation of the open propulsor rotor about an axis, the turbine engine including an engine core, an inlet section, an exhaust section and a flowpath, the engine core including a compressor section, a combustor section and a turbine section, the inlet section comprising a flowpath inlet, the exhaust section comprising a flowpath exhaust and a mixer at the flowpath exhaust, and the flowpath extending from the flowpath inlet, through the inlet section, the compressor section, the combustor section, the turbine section and the exhaust section, to the flowpath exhaust; wherein the mixer is configured to mix combustion products exhausted from the flowpath through the flowpath exhaust with ambient air outside of the propulsion system; and wherein the flowpath exhaust is axially aligned with the open guide vane structure.
14. 14 . A propulsion system for an aircraft, comprising: a propulsion section comprising a propulsor rotor, wherein the propulsor rotor comprises an open propulsor rotor, and the propulsion section further comprises a guide vane structure axially next to and downstream of the propulsor rotor; a compressor section; a combustor section; a first turbine section; a second turbine section configured to drive rotation of the propulsor rotor about an axis; an exhaust section including a plurality of exhaust outlets and a plurality of mixers, the plurality of exhaust outlets arranged circumferentially about the axis, and each of the plurality of mixers located at a respective one of the plurality of exhaust outlets to mix combustion products exhausted through the respective one of the plurality of exhaust outlets with another flow of air; and a flowpath extending from a flowpath inlet, through the compressor section, the combustor section, the first turbine section, the second turbine section and the exhaust section, to the plurality of exhaust outlets.

Description

BACKGROUND OF THE DISCLOSURE 1. Technical Field This disclosure relates generally to an aircraft propulsion system and, more particularly, to an open rotor aircraft propulsion system. 2. Background Information Various types and configurations of aircraft propulsion systems are known in the art including those with an open propulsor rotor. While these known aircraft propulsion systems have various benefits, there is still room in the art for improvement. SUMMARY OF THE DISCLOSURE According to an aspect of the present disclosure, a propulsion system is provided for an aircraft. This propulsion system includes a propulsion section and a turbine engine. The propulsion section includes an open propulsor rotor and an open guide vane structure disposed next to the open propulsor rotor. The turbine engine is configured to drive rotation of the open propulsor rotor about an axis. The turbine engine includes an engine core, an inlet section, an exhaust section and a flowpath. The engine core includes a compressor section, a combustor section and a turbine section. The inlet section includes a flowpath inlet. The exhaust section includes a flowpath exhaust and a mixer at the flowpath exhaust. The flowpath extends from the flowpath inlet, through the inlet section, the compressor section, the combustor section, the turbine section and the exhaust section, to the flowpath exhaust. The mixer is configured to mix combustion products exhausted from the flowpath through the flowpath exhaust with ambient air outside of the propulsion system. According to another aspect of the present disclosure, another propulsion system is provided for an aircraft. This propulsion system includes a propulsion section and a turbine engine. The propulsion section includes an open propulsor rotor. The turbine engine is configured to drive rotation of the open propulsor rotor about an axis. The turbine engine includes an engine core, an inlet section, an exhaust section and a flowpath. The engine core includes a compressor section, a combustor section and a turbine section with the turbine section located between the compressor section and the open propulsor rotor along the axis. The inlet section includes a flowpath inlet. The exhaust section includes a flowpath exhaust and a mixer. The mixer at least partially forms the flowpath exhaust and includes a plurality of mixer projections arranged circumferentially along the flowpath exhaust. The flowpath extends from the flowpath inlet, through the inlet section, the compressor section, the combustor section, the turbine section and the exhaust section, to the flowpath exhaust. According to still another aspect of the present disclosure, another propulsion system is provided for an aircraft. This propulsion system includes a propulsion section, a compressor section, a combustor section, a first turbine section, a second turbine section, an exhaust section and a flowpath. The propulsion section includes a propulsor rotor. The second turbine section is configured to drive rotation of the propulsor rotor about an axis. The exhaust section includes a plurality of exhaust outlets and a plurality of mixers. The exhaust outlets are arranged circumferentially about the axis. Each of the mixers is located at a respective one of the exhaust outlets to mix combustion products exhausted through the respective one of the exhaust outlets with another flow of air. The flowpath extends from a flowpath inlet, through the compressor section, the combustor section, the first turbine section, the second turbine section and the exhaust section, to the exhaust outlets. The propulsor rotor may be configured as or otherwise include an open propulsor rotor. The propulsion section may also include a guide vane structure axially next to and downstream of the propulsor rotor. The mixer may be configured as or otherwise include a chevron mixer. The mixer may be configured as or otherwise include a serrated edge mixer. The flowpath exhaust may include an exhaust outlet. The mixer may form an outer peripheral boundary of the exhaust outlet. The flowpath exhaust may include an exhaust outlet. The mixer may form an inner peripheral boundary of the exhaust outlet. The flowpath exhaust may include an exhaust outlet. The mixer may include a plurality of mixer projections arranged circumferentially about the exhaust outlet. The mixer projections may be configured as or otherwise include a plurality of chevrons. The mixer projections may be symmetrically arranged circumferentially about the exhaust outlet. The exhaust outlet may be non-annular. The exhaust outlet may be annular and the mixer projections may be arranged circumferentially along an outer side of the exhaust outlet. The mixer may also include a plurality of inner mixer projections arranged circumferentially along an inner side of the exhaust outlet. The flowpath exhaust may be formed collectively by a plurality of exhaust outlets. The mixer may be one of a plurality of mix