1. A penetrating member system for injecting a medicament to a body part, comprising:
a housing;
a penetrating member positioned in the housing, the penetrating member including a widened portion and a tip;
a medicament injection source configured to be coupled to the penetrating member
a deformable member sealing the housing;
wherein, during a medicament injection movement of the penetrating member, the tip pierces the deformable member to produce an opening in the deformable member, the widened portion contacting the deformable member during the injection movement and enlarging the opening; and
a cover sheet with a proximal surface with a spatial separation from a distal surface of a lancet cartridge body at a penetrating member channel site, the spatial separation of the proximal surface of the cover sheet from a distal surface of the lancet cartridge body being between the two surfaces that is formed into the distal surface of the lancet cartridge body,
the deformable member configured to reseal after the penetrating member tip has penetrated it while injection medicament from the medicament injection source; wherein, during the injection movement, the portion of the deformable member pierced by the tip becomes flared.
2. The penetrating member system of claim 1, wherein after the injection movement, the tip retracts into the housing and the opening substantially maintains its shape after the retraction.
3. The penetrating member system of claim 1, wherein during the injection movement, the deformable member remains substantially intact.
4. The penetrating member system of claim 1, wherein the widened portion is a substantially conical shape.
5. The penetrating member system of claim 4, wherein a radius of the widened portion increases in a direction along the penetrating member away from the tip.
6. The penetrating member system of claim 1, wherein the widened portion is positioned adjacent to the tip.
7. The penetrating member system of claim 1, wherein the penetrating member defines a needle having the tip and the widened portion, the needle being at least partially surrounded by a penetrating member body.
8. The penetrating member system of claim 1, wherein the housing includes a first end and a second end, the first end including the deformable member and the second end having a second film.
9. The penetrating member system of claim 8, wherein the second film is configured to be pierced by an actuator and the penetrating member is adapted to be driven by the actuator during the injection movement to move the tip toward the deformable member.
10. The penetrating member system of claim 1, wherein during the injection movement, the widened portion enlarges the opening to a size that is substantially larger than the size of the tip.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A gas turbine engine counter-rotatable low pressure turbine comprising:
counter-rotatable annular outer and inner drum rotors,
the outer drum rotor rotatably connected to a low pressure shaft wherein the low pressure shaft is the sole shaft operable for transmitting torque and power out of the low pressure turbine,
a plurality of axially spaced apart low pressure outer drum turbine blade rows extending radially inwardly from an outer shell of the outer drum rotor,
the low pressure inner drum rotor including a plurality of axially spaced apart low pressure inner drum turbine blade rows extending radially outwardly from the annular low pressure inner drum rotor,
the low pressure outer drum turbine blade rows being interdigitated with the low pressure inner drum turbine blade rows, and
the inner drum rotor being geared through an epicyclic gearbox for transmitting torque and power produced by the inner drum rotor to the low pressure shaft.
2. A low pressure turbine as claimed in claim 1, further comprising a differential thrust bearing operably disposed between the outer and inner drum rotors.
3. A low pressure turbine as claimed in claim 2, further comprising the gearbox being located aft of the outer and inner drum rotors.
4. A low pressure turbine as claimed in claim 3, further comprising the gearbox having planetary gears rotatably mounted on pins supported by the turbine rear frame.
5. A low pressure turbine as claimed in claim 4, further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
6. A low pressure turbine as claimed in claim 5, further comprising a radially outer roller bearing disposed between the inner drum rotor and the turbine rear frame and a radially inner differential roller bearing disposed between outer and inner drum rotors.
7. A low pressure turbine as claimed in claim 6, further comprising the pins cantilevered off an annular carrier supported by the turbine rear frame.
8. A low pressure turbine as claimed in claim 2, further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
9. A low pressure turbine as claimed in claim 8, further comprising the gearbox being located aft of the outer and inner drum rotors.
10. A low pressure turbine as claimed in claim 9, further comprising a radially outer roller bearing disposed between the inner drum rotor and the turbine rear frame and a radially inner differential roller bearing disposed between outer and inner drum rotors.
11. An aircraft gas turbine engine comprising:
a single stage fan section having a single fan stage having a single fan blade row,
a counter-rotatable low pressure turbine drivingly connected to the single fan stage by a low pressure shaft,
the counter-rotatable low pressure turbine including counter-rotatable annular outer and inner drum rotors,
the outer drum rotor rotatably connected to the low pressure shaft wherein the low pressure shaft is the sole shaft operable for transmitting torque and power out of the low pressure turbine,
a plurality of axially spaced apart low pressure outer drum turbine blade rows extending radially inwardly from an outer shell of the outer drum rotor,
the low pressure inner drum rotor including a plurality of axially spaced apart low pressure inner drum turbine blade rows extending radially outwardly from the low pressure inner drum rotor,
the low pressure outer drum turbine blade rows being interdigitated with the low pressure inner drum turbine blade rows, and
the inner drum rotor being geared through an epicyclic gearbox for transmitting torque and power produced by the inner drum rotor to the low pressure shaft.
12. An engine as claimed in claim 11, further comprising a differential thrust bearing operably disposed between the outer and inner drum rotors.
13. An engine as claimed in claim 12, further comprising the gearbox being located aft of the outer and inner drum rotors.
14. An engine as claimed in claim 13, further comprising the gearbox having planetary gears rotatably mounted on pins supported by the turbine rear frame.
15. An engine as claimed in claim 14, further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
16. An engine as claimed in claim 12, further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
17. An engine as claimed in claim 16, further comprising the gearbox being located aft of the outer and inner drum rotors.
18. An engine as claimed in claim 17, further comprising the pins cantilevered off an annular carrier supported by the turbine rear frame.
19. An engine as claimed in claim 17, further comprising a radially outer roller bearing disposed between the inner drum rotor and the turbine rear frame and a radially inner differential roller bearing disposed between outer and inner drum rotors.
20. An engine as claimed in claim 19, further comprising the pins cantilevered off an annular carrier supported by the turbine rear frame.
21. An aircraft gas turbine engine family comprising:
at least two different engine models having within the family having different size fans andor operational design fan speeds and different epicyclic gearboxes with different gear ratios respectively for maintaining the same relative differential speed between outer and inner drum turbine blade rows of a counter-rotatable low pressure turbine of the different engine models;
each of the engine models includes an aircraft gas turbine engine a single stage fan section having a single fan stage having a single fan blade row and a respective one of the different size fans andor operational design fan speeds,
the counter-rotatable low pressure turbine drivingly connected to the single fan stage by a low pressure shaft,
the outer drum rotor rotatably connected to the low pressure shaft wherein the low pressure shaft is the sole shaft operable for transmitting torque and power out of the low pressure turbine,
a plurality of axially spaced apart low pressure outer drum turbine blade rows extending radially inwardly from an outer shell of the outer drum rotor,
the low pressure inner drum rotor including a plurality of axially spaced apart low pressure inner drum turbine blade rows extending radially outwardly from the low pressure inner drum rotor,
the low pressure outer drum turbine blade rows being interdigitated with the low pressure inner drum turbine blade rows, and
the inner drum rotor being geared through the epicyclic gearbox for transmitting torque and power produced by the inner drum rotor to the low pressure shaft.
22. An engine family as claimed in claim 21, further comprising a differential thrust bearing operably disposed between the outer and inner drum rotors.
23. An engine family as claimed in claim 22, further comprising the gearbox being located aft of the outer and inner drum rotors.
24. An engine family as claimed in claim 23, further comprising the gearbox having planetary gears rotatably mounted on pins supported by the turbine rear frame.
25. An engine family as claimed in claim 24, further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
26. An engine family as claimed in claim 22, further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
27. An engine family as claimed in claim 26, further comprising the gearbox being located aft of the outer and inner drum rotors.
28. An engine family as claimed in claim 27, further comprising the pins cantilevered off an annular carrier supported by the turbine rear frame.
29. An engine family as claimed in claim 27, further comprising a radially outer roller bearing disposed between the inner drum rotor and the turbine rear frame and a radially inner differential roller bearing disposed between outer and inner drum rotors.
30. An engine family as claimed in claim 29, further comprising the pins cantilevered off an annular carrier supported by the turbine rear frame.