Turbine engine including a steam system
A turbine engine for an aircraft includes a fan that rotates to generate a volume of air, a core turbine engine, a nacelle, and a steam system. The core turbine engine includes a combustor that generates combustion gases, and a turbine including a shaft. The combustor and the turbine define a core air flowpath. The fan is drivingly coupled to the shaft. The nacelle circumferentially surrounds the fan and defines a bypass airflow passage between the nacelle and the core turbine engine. The volume of air flows into the bypass airflow passage as bypass air and flows into the core air flowpath as core air. The steam system extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath to add mass flow to the core air. A bypass ratio of the turbine engine is greater than 18:1.
1 . A turbine engine for an aircraft, the turbine engine comprising:
a fan including a plurality of fan blades that rotates to generate a volume of air;
a core turbine engine comprising:
a combustor that combusts compressed air and fuel to generate combustion gases; and
a turbine including a shaft, the combustor and the turbine defining a core air flowpath, and the fan being drivingly coupled to the shaft such that rotation of the turbine causes the fan to rotate;
a nacelle that circumferentially surrounds the fan, the nacelle defining a bypass airflow passage between the nacelle and the core turbine engine, the volume of air from the fan being split and flowing into the bypass airflow passage as bypass air and flowing into the core air flowpath as core air;
one or more core exhaust nozzles extending radially through a downstream section of the nacelle and in fluid communication with the turbine; and
a steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath to add mass flow to the core air, wherein a bypass ratio of the bypass air to the core air is in a range of 18:1 to 100:1,
wherein the combustion gases flow from the steam system and out of the turbine engine through the one or more core exhaust nozzles.
2 . The turbine engine of claim 1 , wherein the bypass ratio is in a range of 25:1 to 85:1.
3 . The turbine engine of claim 1 , wherein the bypass ratio is in a range of 28:1 to 70:1.
4 . The turbine engine of claim 1 , the core turbine engine further comprising a compressor that compresses the core air to generate compressed core air, the compressor being drivingly coupled to the shaft and defining a portion of the core air flowpath.
5 . The turbine engine of claim 4 , wherein the compressor includes a high-pressure compressor and includes a compression ratio in a range of 20:1 to 40:1.
6 . The turbine engine of claim 5 , wherein the turbine includes a high-pressure turbine (HPT) and includes only one stage of HPT rotor blades and HPT stator vanes.
7 . The turbine engine of claim 5 , wherein the compression ratio is in a range of 22:1 to 40:1.
8 . The turbine engine of claim 5 , wherein the compression ratio is in a range of 24:1 to 40:1.
9 . The turbine engine of claim 1 , wherein the core air flowpath is defined between a core inner wall and a core outer wall, the core outer wall being defined by a splitter, and
the bypass airflow passage is defined between a bypass inner wall defined by the splitter and a bypass outer wall defined at the nacelle.
10 . The turbine engine of claim 9 , wherein the core air flowpath defines a core inlet radius from a longitudinal centerline axis of the turbine engine to the core inner wall at a leading edge of the splitter, the bypass airflow passage defines a bypass radius from the longitudinal centerline axis to the bypass outer wall, and the splitter defines a splitter radius from the longitudinal centerline axis to the core outer wall at the leading edge of the splitter, wherein the turbine engine has a take-off thrust rating in a range of 8,000 pounds to 15,000 pounds, in a range of 15,000 pounds to 30,000 pounds, or in a range of 30,000 pounds to 40,000 pounds,
wherein, for the take-off thrust rating in the range of 8,000 pounds to 15,000 pounds, the bypass radius is in a range of 20.00 inches to 25.00 inches, the splitter radius is in a range of 5.00 inches to 12.00 inches, and the core inlet radius is in a range of 4.00 inches to 9.50 inches,
wherein, for the take-off thrust rating in the range of 15,000 pounds to 30,000 pounds, the bypass radius is in a range of 23.00 inches to 37.00 inches, the splitter radius is in a range of 6.00 inches to 17.00 inches, and the core inlet radius is in a range of 5.00 inches to 14.00 inches, and
wherein, for the take-off thrust rating in the range of 30,000 pounds to 40,000 pounds, the bypass radius is in a range of 35.00 inches to 45.00 inches, the splitter radius is in a range of 9.00 inches to 21.00 inches, and the core inlet radius is in a range of 7.50 inches to 17.00 inches.
11 . The turbine engine of claim 1 , wherein the steam system includes a steam turbine that receives the steam to rotate the steam turbine, the steam turbine being drivingly coupled to the shaft to rotate the shaft when the steam turbine rotates, and the steam turbine has an expansion ratio in a range of 2:1 to 6:1.
12 . The turbine engine of claim 1 , wherein the steam contributes 20% to 50% of a total mass flow through the core air flowpath.
13 . The turbine engine of claim 1 , wherein the steam system includes a steam turbine that receives the steam to rotate the steam turbine, the steam turbine being drivingly coupled to the shaft to rotate the shaft when the steam turbine rotates, and an inlet of the steam turbine being downstream of an outlet of the steam turbine with respect to a flow of the combustion gases from the turbine such that the steam flows through the steam turbine in a direction opposite of the flow of the combustion gases.
14 . A turbine engine for an aircraft, the turbine engine comprising:
a fan including a plurality of fan blades that rotates to generate a volume of air;
a nacelle that circumferentially surrounds the fan;
a core turbine engine comprising:
a compressor that compresses a portion of the volume of air to generate compressed air, the compressor including from ten stages to twelve stages and a compression ratio that is greater than 24:1 and less than or equal to 40:1;
a combustor that combusts the compressed air and fuel to generate combustion gases; and
a turbine including a shaft and having only one stage of turbine stator vanes and turbine rotor blades, the compressor, the combustor, and the turbine defining a core air flowpath, and the compressor being drivingly coupled to the shaft such that rotation of the turbine causes the compressor to rotate;
one or more core exhaust nozzles extending radially through a downstream section of the nacelle and in fluid communication with the turbine; and
a steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath to add mass flow to the combustion gases, wherein the combustion gases flow from the steam system and out of the turbine engine through the one or more core exhaust nozzles.
15 . The turbine engine of claim 14 , wherein the compressor includes eleven stages.
16 . The turbine engine of claim 14 , wherein the nacelle defines a bypass airflow passage between the nacelle and the core turbine engine, the volume of air from the fan being split and flowing into the bypass airflow passage as bypass air and flowing into the core air flowpath as core air.
17 . The turbine engine of claim 16 , wherein a bypass ratio of the bypass air to the core air is in a range of 18:1 to 100:1.
18 . The turbine engine of claim 17 , further comprising a splitter positioned at a core inlet of the core air flowpath that splits the volume of air into the core air in the core air flowpath and the bypass air in the bypass airflow passage, wherein the splitter defines a splitter radius at a leading edge of the splitter, the core air flowpath defines a core inlet radius at the leading edge of the splitter, and the bypass airflow passage defines a bypass radius at the leading edge of the splitter, wherein the turbine engine has a take-off thrust rating in a range of 8,000 pounds to 15,000 pounds, in a range of 15,000 pounds to 30,000 pounds, or in a range of 30,000 pounds to 40,000 pounds,
wherein, for the take-off thrust rating in the range of 8,000 pounds to 15,000 pounds, the bypass radius is in a range of 20.00 inches to 25.00 inches, the splitter radius is in a range of 5.00 inches to 12.00 inches, and the core inlet radius is in a range of 4.00 inches to 9.50 inches,
wherein, for the take-off thrust rating in the range of 15,000 pounds to 30,000 pounds, the bypass radius is in a range of 23.00 inches to 37.00 inches, the splitter radius is in a range of 6.00 inches to 17.00 inches, and the core inlet radius is in a range of 5.00 inches to 14.00 inches, and wherein, for the take-off thrust rating in the range of 30,000 pounds to 40,000 pounds, the bypass radius is in a range of 35.00 inches to 45.00 inches, the splitter radius is in a range of 9.00 inches to 21.00 inches, and the core inlet radius is in a range of 7.50 inches to 17.00 inches.
19 . The turbine engine of claim 14 , wherein the steam system includes a steam turbine that receives the steam to rotate the steam turbine, the steam turbine being drivingly coupled to the shaft to rotate the shaft when the steam turbine rotates, and the steam turbine has an expansion ratio in a range of 2:1 to 6:1.
20 . The turbine engine of claim 14 , wherein the steam contributes 20% to 50% of a total mass flow through the core air flowpath.