US-12618363-B2 - Bifurcation air scoop for gas turbine engine

Abstract

A gas turbine engine includes a fan received within a fan case, the fan delivers bypass air into a bypass duct between an inner radial portion of the fan case and an outer radial surface of an inner core housing. The fan also delivers air into the inner core housing. A compressor section, a combustor and a turbine are within the inner core housing. A bifurcation extends radially to connect the inner core housing to the fan case. The bifurcation has a forward opening defining an air scoop. The air scoop separates air into a first airflow chamber connected downstream to a precooler. The precooler also has a connection to receive compressed air from the compressor section. The air in the bypass duct is delivered to the precooler for cooling the compressed air in the precooler. The air scoop also defines a second airflow chamber for delivering cooling air to components within the inner core housing. An aircraft supply system is also disclosed.

Inventors

• Murat Yazici

Assignees

• RAYTHEON TECHNOLOGIES CORPORATION

Dates

Publication Date

20260505

Application Date

20230718

Claims (18)

1. 1 . A gas turbine engine comprising: a fan received within a fan case, the fan delivering bypass air into a bypass duct between an inner radial portion of the fan case and an outer radial surface of an inner core housing, the fan delivering air into the inner core housing; a compressor section, a combustor and a turbine within the inner core housing; a bifurcation extending radially to connect the inner core housing to the fan case; the bifurcation having a forward opening defining an air scoop, the air scoop separating the bypass air into a first airflow chamber connected downstream to a precooler, the precooler having a connection to receive compressed air from the compressor section, the bypass air in the bypass duct delivered to the precooler for cooling the compressed air in the precooler; and the air scoop defining a second airflow chamber for delivering cooling air to components within the inner core housing; and the first airflow chamber is defined centrally and is separated from the second airflow chamber by a lip at a central lateral location within the air scoop.
2. 2 . The gas turbine engine as set forth in claim 1 , wherein the second airflow chamber is defined laterally outwardly on both of two lateral sides of the lip.
3. 3 . The gas turbine engine as set forth in claim 2 , wherein the second airflow chamber is defined radially outwardly and radially inwardly of the lip.
4. 4 . The gas turbine engine as set forth in claim 1 , wherein the second airflow chamber is defined radially outwardly and radially inwardly of the lip.
5. 5 . The gas turbine engine as set forth in claim 1 , wherein the air scoop extending between a radially outer end and a radially inner end, with a first distance defined between the radially outer end and the radially inner end, and a radial distance between a radially outer end of the lip and a radially inner end of the lip being greater than half of the first distance.
6. 6 . The gas turbine engine as set forth in claim 5 , wherein a radially outer end of the second airflow chamber is spaced from a radially inner end of the second airflow chamber by a distance that is also greater than half of the first distance.
7. 7 . The gas turbine engine as set forth in claim 6 , wherein the second airflow chamber connected into a connection receiving a valve.
8. 8 . The gas turbine engine as set forth in claim 1 , wherein the second airflow chamber connected into a connection receiving a valve.
9. 9 . The gas turbine engine as set forth in claim 1 , wherein the second airflow chamber connected into a connection receiving a valve.
10. 10 . An aircraft air supply system comprising: an environmental control system for delivering cabin air to an aircraft cabin; a fan received within a fan case, he fan delivering bypass air into a bypass duct between an inner radial portion of the fan case and an outer radial surface of an inner core housing, the fan delivering air into the inner core housing; a compressor section, a combustor and a turbine within the inner core housing; a bifurcation extending radially to connect the inner core housing to the fan case; the bifurcation having a forward opening defining an air scoop, the air scoop separating the bypass air into a first airflow chamber connected downstream to a precooler, the precooler having a connection to receive compressed air from the compressor section, the bypass air in the bypass duct delivered to the precooler for cooling the compressed air in the precooler; the compressed air is delivered from the precooler to the environmental control system; and the air scoop defining a second airflow chamber for delivering cooling air to components within the inner core housing; and the first airflow chamber is defined centrally and is separated from the second airflow chamber by a lip at a central lateral location within the air scoop.
11. 11 . The aircraft air supply system as set forth in claim 10 , wherein the second airflow chamber defined laterally outwardly on both of two lateral sides of the lip.
12. 12 . The aircraft air supply system as set forth in claim 11 , wherein the second airflow chamber is defined radially outwardly and radially inwardly of the lip.
13. 13 . The aircraft air supply system as set forth in claim 10 , wherein the second airflow chamber is defined radially outwardly and radially inwardly of the lip.
14. 14 . The aircraft air supply system as set forth in claim 10 , wherein the air scoop extending between a radially outer end and a radially inner end, with a first distance defined between the radially outer end and the radially inner end, and a radial distance between a radially outer end of the lip and a radially inner end of the lip being greater than half of the first distance.
15. 15 . The aircraft air supply system as set forth in claim 14 , wherein a radially outer end of the second airflow chamber is spaced from a radially inner end of the second airflow chamber by a distance that is also greater than half of the first distance.
16. 16 . The aircraft air supply system as set forth in claim 15 , wherein the second airflow chamber connected into a connection receiving a valve.
17. 17 . The aircraft air supply system as set forth in claim 10 , wherein the second airflow chamber connected into a connection receiving a valve.
18. 18 . The aircraft air supply system as set forth in claim 10 , wherein the second airflow chamber connected into a connection receiving a valve.

Description

BACKGROUND OF THE INVENTION This application relates to an air scoop for supplying air for two distinct purposes from a bifurcation in a gas turbine engine. Gas turbine engines are known, and typically include a fan delivering air into a bypass duct as propulsion air. An outer fan case surrounds the fan. The fan also delivers air into an inner core housing, and into a compressor section. The air is compressed and delivered into a combustor where it is mixed with fuel and ignited. Products of this combustion pass downstream over turbine rotors, driving them to rotate. As known, a bifurcation extends radially between the inner core housing and the fan case to secure the two. Air is needed for a gas turbine engine for a number of reasons. As an example, the gas turbine engine may also supply air for application and use on an aircraft. In addition, cooling air is typically supplied within the inner core housing. SUMMARY OF THE INVENTION In a featured embodiment, a gas turbine engine includes a fan received within a fan case, the fan delivers bypass air into a bypass duct between an inner radial portion of the fan case and an outer radial surface of an inner core housing. The fan also delivers air into the inner core housing. A compressor section, a combustor and a turbine are within the inner core housing. A bifurcation extends radially to connect the inner core housing to the fan case. The bifurcation has a forward opening defining an air scoop. The air scoop separates air into a first airflow chamber connected downstream to a precooler. The precooler also has a connection to receive compressed air from the compressor section. The air in the bypass duct is delivered to the precooler for cooling the compressed air in the precooler. The air scoop also defines a second airflow chamber for delivering cooling air to components within the inner core housing. In another embodiment according to the previous embodiment, the first airflow chamber is defined by a lip at a central lateral location within the air scoop. In another embodiment according to the previous embodiment, the second airflow chamber defined laterally outwardly on both of two lateral sides of the lip. In another embodiment according to the previous embodiment, the second airflow chamber is defined radially outwardly and radially inwardly of the lip. In another embodiment according to the previous embodiment, the second airflow chamber is defined radially outwardly and radially inwardly of the lip. In another embodiment according to the previous embodiment, the air scoop extends between a radially outer end and a radially inner end, with a first distance defined between the radially outer end and the radially inner end, and a radial distance between a radially outer end of the lip and a radially inner end of the lip being greater than half of the first distance. In another embodiment according to the previous embodiment, a radially outer end of the second airflow chamber is spaced from a radially inner end of the second airflow chamber by a distance that is also greater than half of the first distance. In another embodiment according to the previous embodiment, the second airflow chamber is connected into a connection receiving a valve. In another embodiment according to the previous embodiment, the second airflow chamber is connected into a connection receiving a valve. In another embodiment according to the previous embodiment, the second airflow chamber is connected into a connection receiving a valve. In another featured embodiment, an aircraft air supply system includes an environmental control system for delivering air to an aircraft cabin. A fan is received within a fan case. The fan delivers bypass air into a bypass duct between an inner radial portion of the fan case and an outer radial surface of an inner core housing. The fan also delivers air into the inner core housing. A compressor section, a combustor and a turbine are within the inner core housing. A bifurcation extends radially to connect the inner core housing to the fan case. The bifurcation has a forward opening defining an air scoop. The air scoop separates air into a first airflow chamber connected downstream to a precooler. The precooler also has a connection to receive compressed air from the compressor section. The air in the bypass duct is delivered to the precooler for cooling the compressed air in the precooler. The compressed air is delivered from the precooler to the environmental control system. The air scoop also defines a second airflow chamber for delivering cooling air to components within the inner core housing. In another embodiment according to the previous embodiment, the first airflow chamber is defined by a lip at a central lateral location within the air scoop. In another embodiment according to the previous embodiment, the second airflow chamber defined laterally outwardly on both of two lateral sides of the lip. In another embodiment according to the previous