초록

A gas turbine engine includes a jumper tube that extends through a first passage and a second passage.

대표청구항 ▼

1. A gas turbine engine comprising: an engine case that defines a first passage; anda jumper tube that extends from a bearing support, the jumper tube mounted to said engine case via a flange such that said jumper tube extends through said first passage. 2. The gas turbine engine as recited in claim

1. A gas turbine engine comprising: an engine case that defines a first passage; anda jumper tube that extends from a bearing support, the jumper tube mounted to said engine case via a flange such that said jumper tube extends through said first passage. 2. The gas turbine engine as recited in claim 1, wherein said first component is a fan inlet case and said second component is a #1/#1.5 bearing support. 3. The gas turbine engine as recited in claim 1, wherein said first component is a fan inlet case, said jumper tube in communication with a hollow strut of said fan inlet case, said hollow strut providing a services pathway across a primary airflow path. 4. A gas turbine engine comprising: a first component that defines a first passage; anda jumper tube mounted to said first component via a flange such that said jumper tube extends through said first passage, wherein said jumper tube is resiliently mounted within said first passage via at least one seal. 5. A gas turbine engine comprising: a first component that defines a first passage; anda jumper tube mounted to said first component via a flange such that said jumper tube extends through said first passage, wherein said flange defines an opening in communication with a bore through said jumper tube. 6. A gas turbine engine comprising: a first component that defines a first passage; anda jumper tube mounted to said first component via a flange such that said jumper tube extends through said first passage, wherein said jumper tube includes a lateral opening. 7. The gas turbine engine as recited in claim 6, wherein said lateral opening communicates with one of said first component and said second component. 8. A gas turbine engine comprising: a fan inlet case that defines a first passage, said fan inlet case includes a hollow strut;a bearing support that defines a second passage;at jumper tube mounted to said first component via a flange to extend through said first passage and said second passage to communicate with said hollow strut, said hollow strut providing a services pathway across a primary airflow path. 9. The gas turbine engine as recited in claim 8, wherein said jumper tube includes a lateral opening. 10. The gas turbine engine as recited in claim 9, wherein said lateral opening communicates with said bearing support. 11. The gas turbine engine as recited in claim 8, wherein said flange defines an opening in communication with a bore through said jumper tube. 12. The gas turbine engine as recited in claim 8, wherein said flange defines a distal end of the jumper tube. 13. A method of assembling a gas turbine engine comprising: assembling a first component that defines a first passage to a second component that defines a second passage, said first component and said second component arranged along an engine central longitudinal such that an interface therebetween is transverse to said engine central longitudinal; andinserting a jumper tube through said first passage and said second passage to extend across said interface; andmounting the jumper tube to the first component via a flange, the flange defining a distal end of the jumper tube. 14. The method as recited in claim 13, further comprising resiliently mounting the jumper tube with a multiple of seals within the first passage and the second passage. 15. The method as recited in claim 13, further comprising providing a service pathway through the jumper tube. 16. The method as recited in claim 15, further comprising directing the service pathway through a lateral opening in the jumper tube. 17. A gas turbine engine comprising: a fan inlet case that defines a first passage;a #1/#1.5 bearing support that defines a second passage; andat jumper tube that extends through said first passage and said second passge. 18. A gas turbine engine comprising: a first component that defines a first passage; anda jumper tube mounted to said first component via a flange such that said jumper tube extends through said first passage, wherein said flange defines a distal end of the jumper tube.